Lewis icing research tunnel test of the aerodynamic effects of aircraft ground deicing/anti-icing fluids

Appendix A

Fluid Holdover Time, Rheological Properties, and Water Content

20 *C, 0 °C, - 10 °C, and -25 °C. A Brookfield viscometer

This appendix contains rheological properties and water

content for all fluids tested. The rheological properties and (Model LVT DV-II), a small sample adaptor, and test spindles water content were determined by Boeing Materials SCR4-18/13R (fluid 1 at all temperatures and fluid 4.2 at 0 °C)

and SCR4-34/13R (all fluids except fluid 1 and fluid 4.2 at

Technology. The fluid holdover times were determined by

various sources, as noted in the section below. 0 °C) were used to determine the fluid viscosities. Temperature

control was maintained using Brookfield EX-200 and Neslab

Fluid Holdover Time

coolers. Data were recorded using the Brookfield DV Gather

software program.

The fluid holdover times in freezing rain are shown in table I

Tables IV to XV contain the rheological data for all of the

(p. 4). The data sources are also noted in that table. Holdover

fluids. Some of these data at - 10 °C are shown in the plots

times are shown for the four basic fluids (fluids 1, 2, 3, and

of viscosity versus shear stress of figure 58. The four basic

4). Holdover times are also shown for the four experimental

fluids (fluids 1, 2, 3, and 4) are shown in figure 58(a). The

fluids that were chosen for commercial production (fluids 2.2, eight experimental fluids are shown in figures 58(b) and (c).

3.2, 4.1, and 5.1). The AEA freezing rain endurance test

(ref. 9) was used in all cases.

Fluid Water Content

Fluid Rheological Properties

The water contents of all 12 fluids tested are shown in table

XVI. These results were determined by Boeing Materials

The fluid rheological properties were determined by Boeing

Materials Technology from samples taken during the wind Technology from samples taken during the wind tunnel test.

tunnel test. Viscosities were determined for each fluid at

TABLE IV.--FLU[D 1 RHEOLOGICAL PROPERTIES Shear Ileltl Vel,city at Torque, Viscosity, Shear rotation, percellt cP stress, rate, TABLE V.--FLUID 2 RHEOLOGICAL PROPERTIES secd dylle/¢m 2 rpm -25 °C Telllperattll'e, Shear Item Shear Veh_ily at Torque. Visctr,;ity.

OI 0.3 7.1 711 2.81 0.3 rolaliOlI, percent cP S_I'_SS r i'flle, 5.86 .7 02 .6 14.8 741 S¢.¢ -t dylle/¢lll 2 tpm 03 1.5 37.5 748 14.80 I.Q q'emper:atttre, -25 *C 04 29.70 3.9 3.0 74.9 752 05 1.5 38.4 768 15,20 1.9 01 0.6 3o.1 39 100 65.5 0.1 .7 06 .6 15.8 792 6.26 02 1.5 60.7 24 400 102.0 .4 07 .3 8.2 818 3.23 .3 03 3.0 86.4 17 400 145.0 .8 04 3.0 86.7 17 400 146.0 .8 -10 *C Tetllpel_lttll-e_ 05 t.5 60.9 24 400 102.0 .4 Ot 0.3 1.4 140 0.55 0.3 06 .6 39.8 39 900 66.O .1 02 .6 3.3 166 1.31 .7 Temperature, - 10 *C 03 1.5 9.4 189 3.72 1.9 04 3.0 19.4 1o4 7.68 3.9 21 400 35.8 01 0.6 21.4 0.1 6.0 39.1 195 15.40 7.8 12 600 52.9 02 1.5 31.6 .4 06 12.0 70.1 197 31.30 15.8 8 750 73.4 03 3.0 43.8 .8 07 6.0 40.3 202 16.00 7.9 6 160 103.0 04 6.0 61.6 1.6 08 3.0 20.2 202 7.99 3.9 4 430 148.0 05 12.0 88.4 3.3 09 1.5 10.4 209 4.12 1.9 6 250 105.0 06 6.0 62.3 1.6 I0 .6 4.5 225 1.78 .7 8 020 74.8 07 3.0 44.5 .8 11 .3 2.0 200 .79 .3 13 000 54.3 08 1.5 32.4 .4 22 200 37.2 OO .6 22.2 .1 Ten|perature, 0 *C Temperature, 0 °C ol 0.3 0.6 60.1 0.23 0.3 02 .6 1.6 80.2 .63 .7 01 0.6 15.3 15 300 25.7 0.1 03 1.5 5.0 100.0 1.08 1.9 02 t.5 22.2 8 880 37.2 .4 O4 3.0 9.6 96.2 3.80 3.9 03 3.0 30.5 6 II0 51.2 .8 6.0 18.8 04.2 7.44 7.8 04 6.0 42.4 4 240 71.1 1.6 06 12.0 37.8 04.4 14.90 15.7 05 12.0 60. I 3 020 101.0 3.3 30.0 95. I 95.2 37.60 39.4 06 30.0 98. I I 970 165.0 8.3 08 12.0 38.1 95.2 15.10 15.8 07 12.0 60.4 3 040 102.0 3.3 0o 6.0 19.5 97.7 7.72 7.9 08 6.0 42.7 4 280 71.7 1.6 10 3.0 9.4 94.2 3.72 3.9 09 3.0 30.7 6 180 51.8 .8 II 1.5 5.4 108.0 2.14 1.9 10 1.5 22.8 9 150 38.4 .4 12 .6 1.5 75.2 .59 .7 II .6 15.6 15 600 26.2 .I 13 .3 .9 00.2 .35 .3 Temperatttre, 20 *C 20 °C Tenl[reralure, 01 0.6 7.4 7 410 12.4 0.1 01 0.3 0.2 20.0 0.07 0.3 02 10.1 4 040 16.9 1.5 .4 02 .6 .8 40.1 .31 .7 03 13.9 2 790 23A 3.0 .8 03 1.5 1.8 36.1 .71 1.9 04 19.4 I 040 32.5 6.0 1.6 04 3.0 3.4 34.1 1.35 3.9 05 27.3 1 370 45.9 12.0 3.3 05 6.0 6.1 30.6 2.42 7.9 O6 44.3 885 74.2 30.0 8.3 06 12.0 11.7 29.2 4.62 15.8 07 65.3 655 110.0 60.0 16.7 30.0 28.7 28.7 11.30 39.3 08 30.0 44.5 892 74.8 8.3 08 60.0 57.2 28.6 22.60 70.0 09 27.5 I 380 40.2 12.0 3.3 09 30.0 28.8 28.0 I 1.30 39.4 10 1o.5 1 950 32.8 6.0 1.6 10 12.0 11.8 29.6 4.67 15.7 II 3.0 14.0 2 810 235 .8 I1 0.0 6.2 3 I. I 2.46 7.9 12 IO.4 4 170 17.5 1.5 .4 12 3.0 3.4 34.1 1.35 3.9 13 7.1 7 I00 11.9 .6 .1 13 1.5 1.8 36.1 .71 1.0 .6 .7 35.1 .27 .7 15 .3 .4 40.1 .15 .3

TABLE VI.--FLUID 3 RHEOLOGICAL PROPERTIES TABLE VII.--FLUID 4 RHEOLOGICAL PROPERTIES

1|1_111 Veh,,:ily al T*,,rtlue, Viscosity. Shear Shear Item Shear Shear Velocity at Ttnque, Visc_ity, 1"( _H(" k)ll_ 11¢'1_'(_II( CP lll'_'$,q, rBl(', stress, rate, rotat i,.,z, percent cP rpIll dylle/cln" s¢¢ "l dytw/cm: rpm Temperature. -25 *C Tetnlx'ratur¢, -25 oC ol 0,3 I,i 2 200 1.85 0 01 0.6 6,4 6 410 10.7 0.1 02 .6 2.2 2 200 3,70 . I 03 1.5 4.7 1 890 7,go .4 02 1.5 8,0 3 210 13.4 .4 13.90 .8 04 3.0 8.3 I 660 03 3.0 I 1.0 2 200 18.5 ,8 05 6.0 14.3 1 430 24.00 1.6 04 6.0 15.1 I 510 25,3 1.6 06 12.0 25.0 I 250 42.00 3,3 05 12.0 20.4 1 030 34.4 3.3 07 30.0 51.5 I 030 86.50 8.3 06 30.0 32.3 648 54 3 8.3 08 60,0 89,1 8o2 150.00 t6,8 07 60.0 475 476 79.8 16.7 09 30.0 87.10 8.3 51.8 I 040 08 30.0 32.0 641 53.8 8.3 12.0 25.4 1 280 42.80 3.3 09 12.0 20.2 1 010 33.9 3.3 11 6.0 14.8 I 480 24,80 1.6 12 3.0 8,4 I 6_) 14.10 .8 10 6.0 14.9 1 490 25.0 1.6 13 1.5 4.8 I 920 8,06 .4 3.0 18.0 .8 II 10.7 2 140 14 .6 2.2 2 200 3.70 ,1 12 1.5 85 3 410 14.3 .4 15 .3 2,02 0 1.2 2 400 13 ,6 5,0 5 010 8.4 .1 TemlYermure. - 10 *C Temperature, - I0 *C ol 0.3 1.2 2 400 2.02 0 Ol 0.6 4.6 4 5¢0 7,70 0.I 02 .6 2.1 2 1130 3.53 .1 .4 02 1.5 6.O 2 400 10.10 .4 03 1.5 42 I 690 7.06 03 3.0 7.9 I 580 13.30 .8 04 3.0 68 1 360 11.40 .8 6.0 11.1 1 Jl0 18,60 1.6 04 6,0 10.2 1 020 17.10 1.6 o6 120 183 018 3080 3.3 05 12.0 13.6 680 22.80 3.3 07 30,0 50.40 83 35.3 708 06 30.0 205 41 I 34.40 8.3 08 60.0 98.00 16.7 582 585 07 60.0 28.8 287 48.20 16.7 09 30.0 35.6 715 59 .gO 8.3 08 30.0 20.2 4O4 33.90 8.3 IO 12.0 l8.6 927 31.10 33 O9 12.0 13.3 665 22.30 3.3 11 19.30 1.6 6.0 11.5 1 150 I0 6.0 9.8 982 1630 1.6 12 3.O 7.0 I 400 1180 ,8 II 3.0 7.4 1 480 12.40 .8 13 1.5 4.4 I 770 7.30 .4 14 ,6 2.3 2 300 3.86 .1 12 1.5 5.4 2 170 9.07 .4 o 15 .3 1.6 3 190 2,68 13 35 3 510 5,88 .6 .I Teil|peraKIfe. 0 "C Temperature, 0 *C OL 0,3 2.2 4 410 3 30 o 01 0.6 3.0 3 010 5,04 0.1 O2 ,6 3,3 3 310 5.54 ,I 1.5 02 4.4 I 770 739 .4 03 1.5 5.6 2 240 q.38 .4 03 3.0 5.9 1 180 9,91 .8 04 3.0 8.6 1 720 14.40 .8 04 6.0 8.2 822 05 1.6 13.80 1.6 6.0 12.9 1 290 21.70 O6 12,0 19.9 994 33.30 3.3 05 12.0 10.8 539 18.10 3.3 07 30.0 35.7 715 59.go 83 06 30.0 16.2 326 2730 8.3 08 60.0 56.3 563 94.40 16.7 07 60.0 22.4 224 3750 16.7 Oq 300 35.8 718 60.20 83 08 30.0 16.0 319 26,80 8.4 I0 33.60 3.3 12.0 20.0 I 000 09 12.0 105 526 17.60 3.3 II 6.0 13.0 I 300 21.80 1,6 6.0 10 7.8 782 13.10 1.6 12 3.0 8.5 I 7O0 14.30 .8 I1 3.0 5.6 1 120 .8 9.38 13 1.5 5.9 2 370 9.(41 .4 12 1.5 4.0 1 600 6.72 .4 14 .6 3.5 3 510 5.88 .I 13 .6 25 2 500 4.20 .1 15 .3 2.2 4 410 3.70 0 Tcnlperalm'¢, 20 °C Temperature, 20 *C OI 0.3 2.0 4 010 3 36 o 01 0.6 1.2 1 200 2.02 0.1 02 .6 2l 0 2 ol0 4.87 .I 1.5 02 2.1 842 3 53 .4 03 1.5 4.5 I 800 7-56 .4 03 3.0 3.1 621 5.21 .8 04 3.0 6.5 t 300 I O.go .8 04 6.0 4.6 459 7.70 1.6 05 6.0 .4 _42 15.80 1.6 05 12.0 6.7 336 1130 3.3 O6 12,0 14.0 701 23 50 33 06 30.0 103 210 17.60 8.3 07 30.0 23.9 478 40.00 83 07 60.0 08 60.0 36,3 362 60.80 16,7 14.6 146 2450 16.7 Oq 30.0 24.0 481 40.30 8.3 08 30.0 10.4 200 17 50 8.3 I0 12,0 14.1 705 23.70 3.3 09 12,0 6.8 341 11.40 3.3 II 6.0 9,6 960 16.10 1.6 6,0 10 4.7 471 7.90 1.6 12 3.0 6.5 I 300 I 0.90 .8 11 3.0 3.2 641 5.38 0.8 13 1.5 4,7 1 890 790 .4 12 1.5 2.1 842 3.53 .4 6 2 9 2 o IO 4.87 .1 13 .6 1.3 1 300 2.18 .1 15 .3 21 4 410 3.70 o

TABLE VIII.--FLUID 2.1 RHEOLOGICAL PROPERTIES

TABLE IX.--FLUID 2.2 RHEOLOGICAL PROPERTIES Item Velocity at Torque, Viscosity. Shear Shear rotation, percen! cP stress, rate, 1[_'111 Veh_cily at TtM'que. Visc.sity. Shear Shear I'l'q II dyne/era: sec t rotation, percent cP stress, rate, Temperature. -25 *C rpm dynetcm: sec -t 3.02 0.1 01 0.6 1.8 I 800 -25 °C Tel|lpClsltl ie, 02 1.5 4.6 1 840 7.70 .4 01 0.6 2.3 2 300 3.86 0.1 03 3.0 7.4 1 480 12.40 .8 02 3.0 8.0 1 6(Y,) 13.40 .8 21.70 1.6 04 6.0 12 o 1 290 03 6.0 13.9 1 3o0 23.40 1.6 05 12.0 23.2 1 170 39.20 3.3 04 12.0 24.9 1 240 41.70 3.3 06 30.0 4O. 1 982 82.30 8.3 O5 30,0 52.3 I 050 87,90 8.3 07 60.0 85.7 858 144.00 16.7 06 60.0 91.6 917 154.00 16.7 08 30.0 49.3 985 82.60 8.3 07 52.5 1 050 88.20 8.4 30.0 09 12.0 23.2 1 170 39.20 3.3 08 1 240 41.70 3.3 12.0 24.8 I0 6.0 12,6 I 260 21.10 1.6 0o 6,0 13,8 I 380 23,20 1.6 11 3.0 7.4 1 480 12.40 .8 10 3,0 8.0 1 600 13,40 .8 12 1.5 4,0 1 600 6,72 .4 II 1,5 4.4 t 770 7.30 .4 13 .6 2.2 2 200 3.70 , I 12 .6 1.6 I 600 2.68 .1 Temper,ature. - 10 °C -10 *C Tern l'_el-at true.

OI 0.6 3.2 3 210 5.38 0.1 01 0.6 6,8 6 810 I 1.4 0.1 02 15 5.0 2 370 001 .4 .4 02 1.5 11.8 4 730 19.8 03 3.0 9.8 I 070 16.50 .8 03 18.1 3 640 30.5 ,8 3.0 04 6.0 15,8 1 580 26.50 1,6 04 6.0 28.0 2 810 47.0 1.6 12.0 25.9 1 300 43.70 3.3 05 12.0 43.8 2 100 73.4 3.3 30.0 40,3 985 82.60 8.3 06 30.0 81.0 1 620 136.0 8.3 60.0 80,9 810 136.00 16.7 07 12.0 47.3 2 370 705 3.3 08 30.0 51.4 I 030 86.20 8.3 08 6.0 30.7 3 0o0 51.8 1.6 O0 12.0 27.8 I 300 46.80 3.3 O9 3.0 19.8 3 070 33.3 .8 10 6.0 17.2 1 720 28,80 1.6 10 1,5 13.0 5 210 21.8 .4 II 3.0 10.5 2 100 17,60 .8 tl .6 7.2 7 210 12.1 .I 12 1.5 6.6 2 640 II,10 .4 13 ,6 3.5 3 510 5.88 .I Teml'_'ralttre. 0 *C 01 0,6 6.0 6 010 10.1 0.1 Teml_erature, 0 °C 02 1,5 10.2 40o0 17,1 .4 OI 0.6 2.4 2 200 4.03 0.1 03 3.0 15.4 3 090 25.9 .8 02 1.5 4.7 1 890 7.90 .4 6.0 23.5 2 350 39.5 1.6 03 3.0 75 1 500 12.60 .8 05 12.0 36,1 1 800 60.5 3.3 04 6.0 12.1 I 210 20.30 1,6 O6 30.0 63.2 ! 270 106.0 8.3 12,0 20,8 1 040 35.00 3.3 07 60.0 98.0 982 165.0 16.8 06 30.0 36,4 728 61.00 8.3 08 30.0 64.7 1 300 10o.0 8.3 60.0 57.0 581 97.40 16.7 09 12.0 37.2 1 850 62,4 3.3 08 30.0 36.5 731 61.30 8.3 10 6.0 24.4 2 440 40.9 1.6 09 12.0 19.7 985 33.00 3.3 11 3.0 15.0 3 190 26.8 .8 10 6.0 12.2 1 220 20.50 1.6 12 1.5 10.7 4 290 18.0 .4 II 3.0 7.6 1 520 1230 .8 13 6 7.3 7 310 12.3 .I 12 1.5 4.0 1 o70 8.23 .4 13 .6 2 7 2 700 4.54 ,I 20 *C Tcmlx'rature, 01 0,6 2.7 2 700 4_54 0.1 Teml',erattue, 20 °C 02 1.5 4.7 1 890 7.90 .4 OI 0.6 0.9 902 1.5 I 0.1 03 3.0 "/.I .8 1 420 11.90 02 1.5 1.8 72 I 3.02 .4 04 6.0 10.7 1 070 18.00 1.6 03 3.0 2.0 581 4,87 .8 O5 12.0 16.6 830 27.80 3.3 04 6.0 4.8 481 8.06 1.6 06 30.0 20.4 588 40.30 8.3 05 12.0 7.0 306 13.30 3.3 07 60.0 45.3 454 76.20 16.7 06 30.0 15.2 304 25_50 8.3 08 30.0 29.4 588 49.30 8.3 07 60.0 24.8 249 41.70 16.7 19o 12.0 16.0 830 27.80 3.3 08 30,0 15,2 304 25.50 8.3 I0 6.0 10.8 1 080 18.10 1.6 09 12.0 7,9 396 13.30 3.3 11 3.0 7.1 I 420 I 1.o0 .8 10 6.0 4.8 481 8.06 1.6 t2 1.5 4,8 1 020 8.06 .4 3.0 2.0 581 4.87 .8 13 .6 2.0 2 010 4.87 .I 1.5 1.8 72 I 3.02 .4 13 .6 .0 002 151 .I TABLE X.---FLUID 3.1 RHEOLOGICAL PROPERTIES TABLE XI.--FLUID 31 RHEOLOGICAL PROPERTIES Item Velocity al T_wque, Visc,_ity. Shear Shear Item Veh,city at T_x'qoe, Vi-,c(vdly, Shear Shear mtatlotl, percelll c.P strt'ss, rate, rtltutit)lk i)elX:ellt Cp stress, rate, l'pl}l dyne/era: sec "_ rpm dy,e--/cm: sec _ "]'enll1¢rllrLll'¢, -25 °C Temtwralure. -25 °C 01 0,3 1.1 2 200 1.85 0 01 0.3 0.9 1 800 1.51 0 02 .6 2.0 2 000 3.36 . I 02 .6 18 I 800 3,02 . I 03 1,5 4.4 1 770 7.39 .4 03 1.5 3.8 I 520 6.38 .4 04 3,0 7.5 I 50O 12.60 .8 04 3.0 6.9 1 380 I 1.60 .8 05 6.0 12.9 1 290 21.70 1.6 05 6.0 12A I 240 20.80 1.6 O6 12.0 22.4 I 120 37_50 3.3 06 12.0 22.0 I 100 37,00 3.3 O7 30.0 46.2 925 77.00 8.3 07 30.0 46.8 935 78.40 8.3 08 60.0 80.0 802 134.00 16.7 08 60.0 82.3 825 138.00 16.7 00 30,0 46.2 025 77 60 8.3 09 300 46.8 939 78.70 8.3 10 12.0 225 1 130 37.80 3.3 10 12.0 22.3 I 120 3750 3.3 II 6.0 13.1 I 310 22.00 1.6 11 6.0 12.6 I 260 21.10 1.6 12 3.0 7.5 I 500 12.60 ,8 12 3.0 7,0 I 400 1180 8 13 1,5 4.4 1 770 7.39 ,4 13 I_5 4.0 1 600 6.72 ,4 14 .6 2.0 2 000 3.36 .1 14 .6 1.7 1 700 2.86 . I 15 .3 1.3 2 610 2.18 0 15 3 1.0 2 000 1.68 0 Temperature, - 10 *C Tellll_rUltlre. - 10 *C 4.03 0 Ol 0-3 2.4 4 810 01 0.3 1.7 3 410 2.86 0 .6 5.71 .I 02 3.4 3 410 02 .6 2.8 2 8t0 4.70 .I 03 1.5 6.1 2 440 10.20 .4 O3 1.5 5.4 2 170 9.07 .4 04 3.0 9.6 I 920 16.10 .8 04 3.0 8.7 I 740 14.60 .8 05 6.0 14.0 I 400 25.00 1.6 05 6.0 14.0 1 400 23.50 1.6 06 12.0 3,3 23.5 I 180 3950 O6 12.0 22.8 1 140 38.40 3.3 07 30.0 43.5 868 72.80 8.3 07 30.0 43.4 868 72.80 8.3 08 60.0 70. I 703 118.00 16.7 08 60.0 705 706 I 18.00 16.7 09 30.0 43.7 875 73.40 8,3 (3o 30.0 43.5 868 72.80 8.3 I0 12.0 23.7 l 190 39.80 3.3 10 12.0 33 23.0 I 150 38.60 II 0.0 !.6 15.2 I 520 2550 II 6.0 14.3 I 430 24.00 1.6 12 3.0 .8 9.7 I 940 16.30 12 3.0 8.7 I 740 14.60 ,8 13 1.5 6.3 2 520 10.60 .4 13 1.5 5.7 2 290 9.58 .4 14 .6 3.4 3 410 5.71 .I 14 .6 2.7 2 700 454 .I 15 .3 2.3 4 610 3 86 0 15 .3 2.1 4210 3.53 0 Temperature. 0 °C Teml_-atut_, 0 *C 01 0.3 3.4 6 810 5.71 0 01 0.3 3.3 0 Ol0 5.54 0 8,06 .I 02 .6 4.8 4 810 02 .6 4.8 4 810 8,06 .1 03 15 7,8 3 120 13.1 .4 03 1.5 8.0 3 210 13A0 ,4 O4 3.0 1121 2 250 19,0 .8 04 3,0 I 1.8 2 350 19.80 .8 05 6,0 16.6 I 660 27,8 1.6 05 6.0 17.6 I 770 29.70 1.6 O6 12.0 24.8 1 240 41.7 3.3 06 12.0 26.7 1 340 44.80 3.3 O7 72.5 8.3 07 30.0 43.1 865 30.0 46.9 939 78.70 8.3 16.7 08 O8 60.0 66.2 663 II 1.0 60.0 72,3 725 121.00 163 09. 30.0 43,1 865 72.5 8.3 0O 30.0 46.9 939 78.70 8.3 10 12,0 25.0 I 250 42.0 3.3 10 12.0 26.9 I 340 45.10 3.3 11 28.0 1.6 6.0 16.7 1 670 II 6.0 17.9 l 800 3010 1.6 12 3.0 I 1.3 2 250 19.0 ,8 12 3.0 I 1.8 2 350 I 0.80 .8 13 1.5 7.9 3 170 13.3 ,4 13 15 8.4 3 370 14.10 .4 /4 ,6 5.2 5 210 8,74 .1 14 ,6 4,7 4 710 7.90 .t 15 .3 3.6 7 210 6.05 0 15 .3 3.3 6 610 554 0 Temperature. 20 *C Temperature, 20 °C OI 0,3 2.7 5 410 4.54 0 01 0.3 3.1 6210 521 0 02 6.22 .1 ,6 3.7 3 710 02 .6 4,5 4510 7.56 ,I 03 1.5 5.8 2 320 9.74 .4 03 15 69 2 770 1160 4 04 3.0 8.0 I 600 13.40 .8 04 3.0 o.6 I 920 16.10 .8 05 60 11.4 I 140 1920 1,6 05 6.0 13.8 1 380 23.20 1.6 3,3 O6 12.0 16.5 830 27.80 06 120 20.0 I 000 33.60 3.3 07 27.4 548 45.00 8.3 07 30.0 30 0 33.2 605 55 30 8.3 08 60.0 40.8 409 68.60 I6.7 O8 60.0 49.3 403 82.60 167 00 30.0 27.4 548 45.90 8.3 09 30.0 33.1 665 55.70 83 I0 12.0 I6.5 930 27,80 3.3 10 12.0 19.9 994 33.30 3.3 II 6.0 11.5 I 150 19.';0 1.6 11 6.0 13.7 I 370 23.00 1.6 12 3.0 8.0 1 600 13.40 .8 12 3.0 9,6 1 920 16,10 .8 13 9.74 .4 1,5 5.8 2 320 13 15 6.8 2 720 11.40 .4 14 6.38 .I ,6 3.8 3 810 14 .6 4.4 4 410 7.39 .I 15 ,3 2.7 5 410 4.54 0 15 .3 3.4 6 810 5.71 0 TABLE XIII.--FLUID 4.2 RHEOLOGICAL PROPERTIES TABLE XII.---FLU1D 4,1 RHEOLOGICAL PROPERTIES Veh_ityat I T, Mrque, I Visct,sity, Item Veh,.:ity at Torqt e, Viso:sity, Shear Shear mtaliotx, percen! cP stress, rate.

zutati_uh _ cP rpm rpm dyne/era: sec l Temperature, -25 *C Temfxaalure, -25 *C 0.3 O 210 0.3 9.9 19 900 16.6 0 .6 4 Ol0 8 23 12.7 12 700 213 .I 02 ,6 1.5 3 370 14.10 29.7 .4 03 15 17.6 7 080 04 3,0 2 740 23,00 37.8 .8 04 3.0 22.5 4 510 33,60 1".6 05 6.0 2 000 05 6.0 3O I 3 020 50.7 1.6 51.20 3.3 06 12.0 1 530 72.0 3.3 06 12.0 42.8 2 140 07 30.0 1 060 88.50 8.3 75.6 I 510 127.0 8.4 07 30.0 36.0C [ l_ii 74.8 33 08 60,0 808 08 12.0 44.5 2 240 50.4 1.6 30.0 962 80.60 8.3 ty_ 6,0 30.0 3 010 09 35.6 .8 10 12.0 1 280 42.80 3.3 10 3.0 21.3 4 240 26.2 .4 II 1.5 15.7 6 260 II 6,0 1 610 27.00 I i!i .6 11.4 I I 400 19.2 .I 17.50 12 12 3.0 2 0o0 .3 8.8 17 700 14.8 0 13 13 1.5 2 770 6.72 14 .6 4 010 Temperature, - I 0 *C 11,60 .l 0.. _ 3 5 8 I0 487 Ol 0.3 9.8 lO 700 1650 0 15.00 .I Teml_ralure. - lO °C 02 ,6 8.9 8 920 .4 03 1,5 II .6 4 620 1950 01 0,3 3 6 I0 04 3.0 14,4 2 890 24.20 .8 .6 2 500 05 6.0 18.6 1 850 31.10 1.6 03 1,5 1 600 40.90 33 06 12.0 24.3 I 220 04 3.0 1 220 63 30 83 07 30.0 37,6 755 05 6.0 8o2 08 60.0 62.1 621 104.00 16.7 06 12.0 646 09 30.0 40.3 808 67.80 8,3 07 30.0 46 I 41.20 3.3 1o 12.0 24.6 I 230 08 60.0 37 I 30.20 1.6 11 6.0 18.0 I 800 09 30.0 468 12 3.0 13.6 2 720 22.80 .8 10 12.0 646 10,4 4 170 17.50 .4 13 1.5 II 6.0 842 14 .6 7.1 7 I00 11.90 .1 12 3.0 1 I00 9.74 0 15 .3 5.8 II 600 13 1.5 1 520 Temperttture, 0 °C 14 .6 2 200 01 0.3 6.1 12 200 10.20 .3 3 010 02 .6 7.4 7 410 12,40 .I Tenq_erallne. 0 °C 03 1.5 q.6 3 840 16.10 .4 .8 04 3.0 11.7 2 340 19.70 01 0.3 I 230 05 6.0 14.8 I 408 24.80 1.6 02 .6 817 06 12.0 18.7 935 31.40 3.3 03 1.5 534 07 30.0 27.6 554 46.50 8.3 04 3.0 371 08 60.0 423 424 71.10 16,7 05 6.0 277 o0 30.0 28.5 571 47.90 8.3 06 12.0 215 10 12.0 18.8 935 31.40 3.3 07 6.0 264 1,6 II 6.0 143 I 430 24.00 08 3.0 334 12 3.0 112 2 240 18.80 .8 09 1.5 449 13 1.5 8,8 3 520 14.80 .4 10 .6 581 14 ,6 6.5 6 510 10.o0 .I .3 762 15 .3 8.23 0 4.0 9 820 Temperattue, 20 *C Tempelature, 20 *C 01 0.3 I t_X) 01 0.3 4.7 9 420 7.90 0 O2 .6 802 o2 .6 5.2 5 210 8 34 .I 1.34 ] .1 O3 1.5 601 03 1.5 7.1 2 840 11.90 .4 2.52 ] .4 O4 3.0 46 I 04 3.0 8,6 1 720 14.40 .8 386 [ .8 05 6.0 351 o5 6.0 10,6 I ObO 17.80 1.6 5.88 i 1.6 O6 12.0 265 3.3 06 12.0 13.2 661 22.2O 8,o0 [ 3.3 30.0 187 07 30,0 18.3 367 30.80 8.3 1560 [ 8.3 08 60.0 144 08 60,0 42.30 16.7 25.2 252 2420 I 16.8 09 30.0 8.3 O9 30.0 18O 18.6 371 31.10 15.80 [ 8.3 10 12.0 276 IO 12.0 13,1 656 22.00 3.3 . 9,24 [ 3.3 I1 6.0 10.3 I 030 17.30 1.6 I1 6.0 371 6 22 [ 1.6 12 3.0 8.2 I 640 13.80 .8 12 3.0 481 4,03 [ .8 13 1.5 10.90 .4 6.5 2 610 13 1,5 681 2.80 [ .4 14 .6 4.6 4 500 7.70 .I 14 .6 I 000 1.68 i .I 15 .3 3.6 7 210 6.05 0 .3 I 400 TABLE XIV.--FLUID 5.1 RHEOLOGICAL PROPERTIES TABLE XV.--FLUID 5.2 RHEOLOGICAL PROPERTIES Item lleln Velocity at Tt. qtve, Visc_ity, Shear Shear Veh_city at T_rtlue, Viscosity, Shear Shear petrceHI cP stress, n_ate, i-olai h)II, pel'C e Ill CP stress, tale, tlylle/cm z se¢d I pill dy fie/tin" se_ i l"eBll_'ratllre , --'25 °C l"el|ll_ratlil'e, -25 °C 01 0.3 05 1 000 0.84 0 01 0.3 0.0 1 800 1.51 0 02 .6 J.l I I00 185 .I 02 .6 1.3 1 300 2.18 .I 1.5 21 842 353 4 03 1.5 3.0 1 200 5.04 .4 O4 04 3.0 3,8 762 6.38 .8 3.0 5 2 1 040 8 74 .8 6.0 7,2 721 1210 1,6 05 6.0 9,1 910 15.30 1.6 06 12.0 O6 13,1 656 22,00 3.3 12.0 16.1 807 2 7.00 3,3 07 30.0 07 28.9 578 48.40 8.3 30.0 34.4 b88 57.70 8.3 08 60.0 08 60.0 52.1 521 87.40 16.7 61,7 618 104.00 16.8 O9 30.0 09 30 0 29.0 581 48.70 8.3 358 718 60.20 8.3 10 12.0 3.2 661 22.20 3.3 10 12,0 17 4 8_8 29.10 33 II 6.0 7.1 710 11.90 I.e. II 6.0 lO.I I OlO 1690 16 12 3,0 3.9 782 6.55 .8 12 3.0 5,8 I 160 9.74 .8 13 1.5 13 2.1 842 3.53 .4 1,5 3.3 I 320 5 54 .4 14 .6 I.I I 100 1.85 .I .6 1.8 I 800 3.02 .1 15 .3 15 .3 ..5 I 000 .84 0 t2 2 400 2.02 0 Teml_rature, - I 0 *C Temperahae, - I0 *C 01 0.3 0.3 601 0.50 0 01 0.3 0.7 I 400 1.18 0 02 .6 .6 601 I 01 ,I 02 .6 l.I l 100 1.85 .1 03 1.5 1.3 521 2.18 .4 15 2.2 882 3.70 ,4 04 3.0 2,4 481 4.03 .8 3.0 3.8 762 6.38 .8 05 05 6.0 4.4 441 7,39 1.6 6.0 6_t 631 I 0 60 1.6 O6 12.0 O6 12.0 7.8 391 13.10 3.3 10.6 529 17,80 3.3 07 30.0 16.6 332 27.80 8.3 30.0 21.3 424 35.60 8.3 08 60,0 28,7 287 4820 167 08 60.0 36,0 36 I 60.50 16.7 O9 O9 30.0 10,6 332 27.80 8.3 30.0 21.o 438 30 70 8.3 12.0 7.9 396 13.30 3.3 10 12.0 11.3 566 19.00 3.3 11 6.0 II 4__i 45 1 7.56 l 6 6.0 6.8 68 I 11:40 1.6 12 3.0 12 2.5 501 4.20 .8 3.0 4.1 818 6.86 .8 1.5 I A 561 2,35 .4 13 1.5 2.6 1 040 4.37 .4 14 14 .6 .6 601 I,OI .1 .6 1,4 I 400 2.35 .1 15 .3 15 .3 .3 601 .50 0 .8 1 600 1.34 0 Tenll_lllture. 0 *C Telllperalttte. 0 *C 01 0.3 OI 0.3 0.3 601 0 .50 0 I,0 2 000 1,68 0 02 .6 02 .6 .7 701 1.18 .I 1.3 I 3O0 2.18 .I O3 J5 1.4 561 2.35 .4 03 1.5 2,4 962 4 03 .4 3.0 2.3 461 3.86 .8 04 3.0 3.8 762 6.38 .8 05 6,0 3 .o 391 6.55 1.6 05 6.0 5.9 5Ol 9,91 1.6 12.0 6.7 336 I 1.30 3.3 06 12.0 9,3 466 15,60 3.3 07 30.0 07 30.0 13.4 269 2250 8.3 17.4 347 29.10 8.3 08 08 60 O 60.0 22.6 227 38.10 16.7 28.2 284 47.60 167 (3O 09 30.0 13.4 269 22.50 8,3 30.0 17.6 354 29.70 83 I0 t0 12.0 12.0 95 476 6.7 336 11 .t0 3.3 16.00 3.3 II 6.0 II 6.0 3.9 301 6.55 1,6 6.I 610 10.20 1.6 12 12 3.0 2,3 461 3.86 .8 3.0 3,8 762 6.38 ,8 13 1.5 I 4 561 2,35 .4 13 1.5 2.6 040 4,37 .4 .O .8 802 1.34 A 14 .6 1.6 t_(D 2.68 ,I IS .3 15 .3 .5 I 000 .84 0 IO i: 000 1,68 0 Temlwramre, 20 *C Temlx_ratme, 20 _C 01 0.3 I'1 0.3 0.3 601 0.50 0 1.0 2 000 1.08 0 02 02 .6 .6 601 1.01 . I .6 13 1 300 2.18 .1 03 15 03 1.5 I0 401 1.08 .4 21 842 3.53 4 04 3.0 04 3.0 t,7 341 2.86 .8 3.0 601 5.04 .8 6.0 2.8 281 4.70 1.6 05 6.0 4.5 45 I 7,56 1.6 i 2.0 4 5 225 7.56 3.3 06 120 6.7 336 I 1.30 3._ 07 300 8.7 174 14,00 8.3 07 30.0 I 1.8 235 I 0.80 08 60.0 14,3 143 24.00 16.7 08 60.0 18.3 184 30.80 16 7 09 30.0 8.7 174 14.00 8.3 09 30.0 11.8 235 19.80 8.4 10 120 45 225 756 3.3 10 12.0 6.8 34 I I 1.40 3.3 II 6.0 I1 2.7 270 4.54 1.6 6.0 4.5 45 I 7,56 1.6 12 3.0 12 3.0 1,7 34t 2.86 .8 3.0 601 5.04 .8 13 1.5 13 1.5 1,0 401 1.68 .4 2, I 842 3.53 .4 t4 14 .6 .6 601 1.01 . I .6 1.3 t 300 2.18 .I 15 .3 15 .3 .3 60 [ .50 0 .9 1 800 1.51 0 12 000 10 000 8 000 I Fluid 6 000 4 000 2 000

I (a)l

TABLE XVI.--WATER CONTENT OF DEICING AND ANTI-ICING 12 000 F Fluid FLUIDS

I

10 000 _-- • 3.2 Fhlid Water l.'liiii ellll.

pet_:etlt

• 4.1

(n) I 9.9 I1_ tl 2 46,7 6 000 2. I 45.8 O 2.2 44 4

It

4 000 3 43.0 8 000 --_ 3.t 42.3 3 2 42,3 2 O00 ___El 4 43.0 4.1 36.4

o - I = _I (b)l

4.2 42.0 5.1 49.0 5,2 48 6 12 000 -- Fluid '.4reticle _)i three i'Itlll_;, 10000 -- • 3.1 0 5.2 • 4.2 8000 -- r-I 2.1 4 0O0 2 000 6000 _

(c) I

0 40 80 120 160 Shear stress, dyne/cm2 Figure 58--Fluid viscosity versus shear stress. Fluid temperature, -10 °C.

Next: Appendix B →

Appendix B

Three-Dimensional Half Model Force Data

the fluid effects under these free air conditions. Therefore, This appendix contains the three-dimensional model force runs were made with the ground plane removed for both the data. The data are divided into the following categories: (1) flaps 5 and flaps 15 configurations. This was done only for data in ground effect (ground plane in); (2) data in free air fluid 3 at 20 °C. The results are shown in figure 67.

(ground plane out); (3) effect of miscellaneous parameters; and (4) test technique verification. Some lift data are adjusted Effect of Miscellaneous Parameters for initial balance offset, which is present due to balance drift from the applicable wind off zero. This correction to the data The effects of miscellaneous parameters such as initial fluid is explained in appendix E.

depth, final velocity, fluid chordwise coverage, gaping the slat on the flaps 5 configuration, aileron deflection, and cleaning Data in Ground Effect the underside of the slat after application of the fluid are shown in figures 68 to 73. The effect of initial fluid depth (fig. 68) Because the ground acts as a reflection plane, the aero- was investigated early in the test when the model was being dynamics of the airplane are different near the ground than rotated to a particular fixed angle of attack on each run. That they are in free air. Therefore, to properly simulate this effect, is why the data shown in these two figures only go to 7°. The most of the three-dimensional half model testing was done with same explanation applies to the data on the effect of final the ground plane in. The ground plane was described earlier velocity (fig. 69).

in this report (see "Models and Installation").

Flaps 5, sealed slats.--The three-dimensional half model Test Technique Verification configuration that was investigated most extensively was the flaps 5, sealed slat. This is the most common takeoff flap As discussed earlier (see "Test technique verification" setting used on the 737-200ADV. All four of the basic fluids section in the main text), the original test plan called for were tested on this configuration. The range of temperatures rotating the model to a fixed attitude and holding that attitude tested varied from fluid to fluid. For some of the fluids two for the duration of the run. The attitude would be changed sets of data were taken at a given temperature. These repeat from run to run in order to define points on the lift curve.

runs were usually separated by a large number of runs. In these The purpose of this approach was to match the procedures of cases, both the dry baseline and the fluid runs were repeated the Kuopio flight test. However, as noted previously, it was to account for any long-term balance shifts that might have determined during testing that it was possible to obtain the occurred. The data are shown in figures 59 to 62. For each entire lift curve during a single run by rotating the model fluid the data are arranged in order of decreasing temperature.

continuously to an attitude above that corresponding to Flaps 15, gapped slats.--Data were obtained for all four Q.max- Figure 74 show the results of runs made to verify that of the basic fluids on this configuration. These results are this test technique worked for each of the four basic fluids.

shown in figures 63 to 66.

In these figures the symbols indicate the maximum angle of attack for a given run. However, data are taken continuously Free-Air Data as the model is rotated so that data are obtained at all angles of attack up to the maximum for a given run. Each of the runs After the airplane lifts off and begins to climb, it very trace out essentially the same curve up to the maximum angle quickly moves out of ground effect. It then is considered to of attack for a given run. Thus, by rotating the model to an be in free air. Since both the flight data and the results from angle of attack beyond stall, all of the data can be obtained this test show that there is still fluid left on the wing during in a single run.

the early portion of the climbout, it is important to understand I

1618 !i

_T r *- i

1.4 L-_-- -E-- i

1.2 F- 1.0 .8 .6 .4 :!

.2 .06 .10 .14 .18 .22 .26 .2 .1 0 -.1 -.2 -.3 --4 0 4 8 12 16 1.8

E

1.6 t:!_i: 1.4 (3

1.2 E

E: (D 1.0

_ :i-_ =Ii:t-

i _E

i _ iiii

O .8 ._1 .6 .4

L_ L_

_ ' _ il!i:!i

i . 'l, I I , i .2 i .06 .10 .14 .18 .22 .26 .2 .1 0 -.1 -.2 -.3 -4 0 4 8 12 16 1.8 i 1.6 1.4

i

1.2 1.0

.... i _ti!

i i i .8 i .6

,r

.4 _x_ .2 .04 .08 .12 .16 .20 .24 .2 .1 0 -.1 -.2 -.3 -4 0 4 8 12 16 Body waterline angle of Pitching moment, CM,0.25 _ Drag coefficient, CD, SA attack, o( B, deg (a) Air temperature, -10 °C; early run.

(b) Air temperature,-10 °C; later run.

Figure 59.--Aerodynamic effects of fluid 1 on three-dimensional half model in flaps 5, sealed-slat configuration. Ground plane in.

1.8 " LI 4 i < :--. -,-4r ; i - \i _i ' ! l; _ 1.0 : i- j'_] ill;! -) ! :_;;:!!

! 7-:1 i- 15 _ :l, I ;_:q

_i tY!_ ... 17;!_ _!

ii

'-'_'_ 7)_' iI:(,,)m

.,_ .2 .2 .1 0 -.1 -.2 -.3 _- -4 0 4 8 12 16 Qi

1i! ¸

ii:i_

ii:!!,!

I_II _'_>I _- __i -

1.4 '_{ i l/l' _'i ii,:.

...... :i

A .....

tL

,<j:,<:i:.: 7: ....

.o i: s_

!I!

!711_

7 i.......

i;7: i_i

.6 777! 4 77;_ }14-:;;k:7tb't: i;[[

[i!' "l:)'!:f !

........

i7]{; !77.. i. _7 i_{7;l 77

.2 :}- :_ .10 .|4 .18 .22 .26 .2 .1 0 -.1 -.2 -.3 .06 -4 0 4 8 12 16 Body waterline angle of Pitching moment, CM,0.25 _" Drag coefficient, CD, SA attack, c_ B, deg (a) Air temperature,-10 °C; early run.

(b) Air temperature, -10 °C; later run.

Figure 60.--Aerodynamic effects of fluid 2 on three-dimensional half model in flaps 5, sealed-slat configuration. Ground plane in.

5o 1.8

E

1.6 1.4 t 1.2

K

1.0

.8i I .6

.4 L4- _-4M -4 4 8 12 16 .06 .10 .14 .18 .22 .26 .2 .1 0 -.1 -.2 -.3 1.8 L:- [_,

:i r __i :: _

1.6 _,

_4 !

I' .....

1.2 i 0,) "_ 1.0 i:

i'

O .8 i (b T :,,-.

.6 _i :i :_"J'l_ _, ) , = : ; , i = i

.4 _

-,t:f I .&

, .2 I- -4 4 8 12 16 .2 .1 0 -.1 -.2 -.3 .06 .10 .14 .18 .22 .26

1.8 _ , _tl ........ I t

1.6

i ! ! i

1.4 _ 1.2

,i

1.0 ,; !il ._, t i_ _.- .8

--i-_ i i;÷i' I: :'_. _J

.6 J _-_'t 3. .....

_i_ : .4 i_, i!!:_-ir:i i !I: .2 ---,i 4 8 12 16 .04 .08 .12 .16 .20 .24 .2 .1 0 -.1 -.2 -.3 Body waterline angle of Drag coefficient, CO,SA Pitching moment, CM, o.25 E attack, (XB, deg (a) Air temperature, 0 °C. Lifldata adjusted for initial balance offset.

(b) Air temperature, -10 °C.

Figure 61 .--Aerodynamic effects of fluid 3 on three-dimensional half model in flaps 5, sealed-slat configuration. Ground plane in.

1.8 1.6 1.4 1.2 1.0 .8 .6 .4

i

.2 -4 0 4 8 12 16 • 06 ,10 .14 .18 .22 ,26 .2 .1 0 -.1 -.2 -.3 1.8

Iiti i , !i

4-'

!i

• i t : -I i!!!-_ 'il + =, i; . J + ;i _i:i: .4 .06 .10 .14 .18 .22 .26 .2 .1 0. -.1 -.2 -.3 4: [ ......... _: 3 ..'.

I! [ =¸ I = .:,'!j /!_ ¸¸¸_+ 4----

_-_i _- _

/ , :i + ' '{ J I J: [ ' I £: _ii =!i_ i;¸ Z[, .....

i_i_ i _

+ _= 4:_l t," t t .04 .08 .12 .16 .20 .24 .2 .1 0 -.1 -.2 -.3 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 E attack, eB, deg (a) Air temperature, -5 °C. Dry lift data adjusted for initial balance offset.

(b) Air temperature, -10 °C.

Figure 62.--Aerodynamic effects of fluid 4 on three-dimensional half model in flaps 5, sealed-slat configuration. Ground plane in.

i .08 .12 .16 .20 .24 .28 0 -.1 -.2 -.3 -.4 -.5 -4 0 4 8 12 16 .06 .10 .14 .18 .22 .26 0 -.1 -.2 -.3 -.4 -.5 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 E attack, eB, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 63.--Aerodynamic effects of fluid 1 on three-dimensional half model in flaps 15, gapped- slat configuration. Ground plane in.

2.2

2.0 ;, :i: _ :l: .:. _, 1.8 ¢o 1.6 I r" 1.4 _-tl _ _':_: _.,':_i: :::-: ::_-!; i _:-± __1

1.o _:_:i.:: _i.:-_,:_F!

.6 _ :_ : !_" ':_ -4 0 4 8 12 16 .08 .12 .16 .20 .24 .28 0 -.1 -.2 -.3 -.4 -.5 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 E attack, (_B, deg Figure 64.--Aerodynamic effects of fluid 2 on three-dimensional half model in flaps 15, gapped- slat configuration. Ground plane in; air temperature, -10 °C.

i i i r j _ I I f ! l I 2.0 _ :" _ __! : _;_'J _:: "=_ _ "- .....

!:_i _'_ ' _:_ _ _ -_-_-_Z i

1.2 :i ..... ,:: : _--- =:=_! _ _ _F"_i4 -f:i-: : i ; { :- ', i 1.o ,,, t- -4 0 4 8 12 16 .08 .12 .16 .20 .24 .28 0 -.1 -.2 -.3 -.4 -.5 6) ...J 2.0 -- : : , - , • :;: !, : i. J 1.4 i :,i:_ _ ;i i ...... T_ i .6 I -4 0 4 8 12 16 ,06 10 14 .18 ,22 ,26 0 -I -2 -.3 -4 -.5 Body waterline angle of Drag coefficient, CD,SA Pitching moment, CM, O.25. E attack, _B, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 65.--Aerodynamic effects of fluid 3 on three-dimensional half model in flaps 15, gapped- slat configuration. Ground plane in.

2.2 2.0 1.8 1.6 1.4 1.2 1.0 (a) .08 .12 .16 .20 .24 .28 0 -.1 -.2 -.3 -.4 -.5 1.0 .8 .6 -4 0 4 8 12 16 .06 .10 .14 .18 .22 .26 0 -.1 -.2 -.3 -.4 -.5 Body waterline angle of Drag coefficient, CD,SA Pitching moment, CM,0.25. E attack, c_ B, deg (a) Air temperature, -5 °C.

(b) Air temperature, -20 °C.

Figure 66.--Aerodynamic effects of fluid 4 on three-dimensional half model in flaps 15, gapped- slat configuration. Ground plane in.

Z i'i, i_!: ; :V/ ,i: _- ....

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(b) In flaps 15, gapped slat configuration.

Figure 67.--Aerodynamic effects of fluid 3 on three-dimensional half model in flaps 15, gapped- slat configuration. Free air; temperature, -20 °C.

1.6 1.4

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Bodywaterline angle of

attack,eB, deg

(a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure68.=Effect of initial fluid depthon aerodynamic effects of fluid 3 on three-dimensional half model in flaps 5, sealed-slat configuration. Ground plane in.

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Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 E attack, _B, deg Figure 69.--Effect of final velocity on aerodynamic effects of fluid 3 on three-dimensional half model in flaps 5, sealed-slat configuration. Ground plane in; air temperature, -10 °C.

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1.4 1.2 ¢=

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2.0

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.4 .2 -1 3 7 11 15 19 .1 0 -.l -.2 -.3 -.4 .06 .10 .14 .18 .22 .26 Body waterline angle of Pitching moment, CM,0.25 _- Drag coefficient, CD, SA attack, eB, deg Figure 71 .--Aerodynamic effects of fluid 3 on three-dimensional half model in flaps 5, gapped-slat configuration. Free air; temperature, -20 °C 1.8 i? i, 1.6 1.4 . 1.2 i_ 1.0 2L

iii

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.2 -4 0 4 8 12 16 .04 .08 .12 .16 .2 .1 0 -.1 -.2 -.3 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 _-

attack, _a, deg

Figure 72._Aerodynamic effects of fluid 3 on three-dimensional half model in flaps 5, gapped-slat configuration. Comparison of 0 and 20 ° aileron deflections. Free air; temperature, -20 °C.

2.4

2.2

2.0 _- 1.8

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c" Q) _E 1.4 Q) t,,) 1.2 ._1 1.0 .8 .6 .0 -.1 -.2 -.3 -.4 -.5 -2 2 6 10 14 18 • 10 •14 •18 .22 .26 .30 Pitching moment, CM,0.25 _- Body waterline angle of Drag coefficient, CD, SA attack, eB, deg Figure 73.-- Aerodynamic effects of fluid 3 on three-dimensional half model in flaps 15, gapped-slat configuration. Free air; temperature, -20 °C.

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_2 -4 0 4 8 12 16 •04 .08 .12 .16 .20 .24 .2 .1 0 -.1 -.2 -.3 Body waterline angle of Drag coefficient, CD,SA Pitching moment, CM,0,25 E.

attack, eB, deg (a) Fluid 1, temperature,-20 °C.

(b) Fluid 2, temperature, -10 °C.

Figure 74._Test technique verification for three-dimensional half model in flaps 5, sealed-slat configuration. Symbols indicate highest _B point of a given run.

_ . _ -i ¸ .1• + i i , F T .Z

_zZ

-I : L i ; 7: .04 .08 .12 .16 .20 .24 .2 °1 0 --.'l --.2 --.3

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(e) Fluid 4, temperature, -20 °C.

Figure 74.--Concluded.

Next: Appendix C →

Appendix C

Two-Dimensional Model Force Data

This appendix contains the two-dimensional model force 22 sec, with rotation at 18 sec at a speed of about 41,1 m/sec (80 keas). The results are shown in figure 83.

data. The data are divided into the following categories: (1) effects of basic fluids (fluids 1 to 4), (2) effects of experimental fluids, (3) effects of miscellaneous parameters, and (4) test Experimental Fluid Data technique verification. Most of these data were corrected for Lift, drag, and pitching moment data for the experimental dynamic pressure q effects. This correction is explained in fluids on the flaps 5, seated-slat configuration are shown in appendix E.

figures 84 to 91. The data are arranged by fluid. For a given fluid, the data are arranged in order of decreasing temperature.

Basic Fluid Data Flaps 5, sealed slats.--Figures 75 to 78 show lift drag and Miscellaneous Data pitching moment data arranged by fluid. For a given fluid, the data are arranged in order of decreasing temperature. Figure 92 to 96 show data for the following: (1) effect of initial Flaps 15, gapped slats.--These results are shown in figures fluid depth; (2) effect of time to rotation (fig. 93), (3) effect 79 to 82. Because of a balance problem that existed when this of rotation velocity; (4) gapped-slat data for the flaps 5 configuration was being tested, there are no drag data at most configuration; and (6) simulated frost data.

conditions.

Flaps 15, cruise leading edge.--To investigate fluid effects Test Technique Verification on a configuration without a leading edge high lift device, several runs were made with a flaps 15, cruise leading-edge Figure 97 shows results from runs made to verify the test configuration. Since this configuration is more typical of a technique of obtaining data over the entire angle of attack range smaller, slower airplane, the tunnel acceleration was changed in a single run. This was done for both the flaps 5, sealed-slat to increase from 11.3 to 46.3 m/sec (22 to 90 keas) in about configuration and the flaps 15, gapped-slat configuration.

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±

2.8 2.4 2.0 1.6 1.2 .8 .4 -.18 -.20 -.22 -.24 -.26 -•28 .02 .06 .10 .14 .18 .22 -2 2 6 10 14 18 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 E attack, ccB, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 75.--Aerodynamic effects of fluid 1 on two-dimensional half model in flaps 5, sealed-slat configuration. Data corrected for dynamic q effects

3.2

2.8

ii i-

2.4 _ _"i"_

t! :t

• 'i .......

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1.2 _ _

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o !i _!_

t- -2 2 6 10 14 18

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.=_

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1.6

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.8 ii

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.02 .06 .10 .14 .18 .22 -. 18 -.20 -.22 -.24 -.26 -.28 -2 2 6 10 14 18 Pitching moment, CM,0.25 E Body waterline angle of Drag coefficient, CD, SA deg attack, eB, (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 76._Aerodynamic effects of fluid 2 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

3.2

Z

2.8 T 2.4 2.0 --4 i ; 1.6 1.2 Z .8

H

.4 2 6 10 14 18 .20 -.20 -.22 -.24 -.26 -.28 -.30 32--- i 2.8_" : :! t ;ii .....

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d

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1.2_ iq 2 6 10 14 18 .20 -.20 -.22 -.24 -.26 -.28 -.30 3.2 2.8 2.4 2.0 1.6 1.2 .8 .4 I '1 2 6 10 14 18 0 .04 .08 .12 .20 -.20 -.22 -.24 -.26 -.28 -.30 Bodywaterlineangleof Drag Pitching moment, CM,0.25 E a_ack,_s, deg (a) Air temperature, -10 °C.

(b) Air temperature, 0 °C.

Figure 77.--Aerodynamic effects of fluid 3 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects :TI L=- • =;:=_ t , , ! _'"" /

tls!i

X :1 t71: -4" J ¢0 -!

I:= 2 6 10 14 18 • 02 .06 .10 .14 .18 .22 -.18 -.20 -.22 -.24 -.26 -.28 "to _E o -.18 -.20 -.22 -.24 -.26 -.28 -2 2 6 10 14 18 Body waterline angle of Pitching moment, CM,0.25E attack, _B, deg (d) Air temperature, -20 °C.

(e) Air temperature, -29 °C.

Figure 77.--Concluded.

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(b) Air temperature, -10 °C.

Figure 78.--Aerodynamic effects of fluid 4 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

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_._ _. I

2i!H2i 12 ' _

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(d) Air temperature, -20 °C; runs 498 and 500.

Figure 78.--Concluded.

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3.4 3.0 2.6 2.2 .... i i 1.8 i 1.0 -2 2 6 10 14 18 -.3 -.4 -.5 -.6 -.7 -.8 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 E attack, _B, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 79,_Aerodynamic effects of fluid 1 on two-dimensional model in flaps 15, gapped-slat config- uration. Data corrected for dynamic q effects.

?1 -.3 -.4 -.5 -.6 -.7 -.8 2.6 1.0 -.3 -.4 -.5 -.6 -.7 -.8 -2 2 6 10 14 18 Body waterline angle of Drag coefficient, CD,SA Pitching moment, CM,0.25 _- attack, _B, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 80.mAerodynamic effects of fluid 2 on two-dimensional model in flaps 15, gapped-slat config- uration. Data corrected for dynamic q effects.

?2 i; c" --,3 -.4 -.5 -.6 -.7 -.8 G) _E .._J -2 2 6 10 14 18 .02 .06 .10 .14 .18 .22 -.3 -.4 -.5 -.6 -.7 -.8 Pitching moment, CM,0.25 E Body waterline angle of Drag coefficient, CD, SA attack, C_B, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 81 .--Aerodynamic effects of fluid 3 on two-dimensional model in flaps 15, gapped-slat config- uration. Data corrected for dynamic q effects.

:!i.:i H?I i:_:_'

:i _i _ t lt :! i: i; ' Ii _:: _ ........

,=, _:

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-.3 -.4 -.5 -.6 -.7 -.8 O O .-I Body waterline angle of attack, _B, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 82.--Aerodynamic effects of fluid 4 on two-dimensional model in flaps 15, gapped-slat contig- uration. Data corrected for dynamic q effects.

2.6

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(b) Air temperature, -10 °C.

Figure 83.--Aerodynamic effects of fluid 3 on two-dimensional model in flaps 15, cruise leading-edge configuration. Data corrected for dynamic q effects ?5 3.2 _i _ I_]¸,:i i¸¸¸¸!ir ii_iT, 2.8 _'_ I"-, i r: _-..,._

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(b} Air temperature, -20 °C.

Figure 84._Aerodynamic effects of fluid 2.1 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

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(b) Air temperature, -20 °C.

Figure85.--Aerodynamic effects of fluid 2.2 on two-dimensional model in flaps 5, sealed-slatconfig- uration. Data corrected for dynamic q effects.

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(b) Air temperature, -10 °C.

Figure 86.--Aerodynamic effects o! fluid 3.1 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

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:ii:_: :_?':_ !:,:i:1!,:,i

I _,-_l J1 _ i_ i- .02 .06 .10 .14 .18 ,22 -.18 -.20 -.22 -.24 -.26 -.28 ..J 2 6 10 14 18 -.18 -.20 -.22 -.24 -.26 -.28 Body waterline angle of Pitching moment, CM,0.25 _ attack, ++B, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 87.--Aerodynamic effects of fluid 3.2 on two-dimensional model in tlaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

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(b) Air temperature, -10 °C.

Figure 88.--Aerodynamic effects of fluid 4.1 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

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(b) Air temperature, -20 °C.

Figure 89.--Aerodynamic effects of fluid 4.2 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

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(b) Air temperature, -10 °C.

Figure 90.--Aerodynamic effects o! fluid 5.1 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

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.8

:T;ii- i:iIi

.4 _ 0 _ -2 .02 .06 .10 .14 .18 .22 -.18 -.20 -.22 -.24 -.26 -.28 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 E attack, _B, deg (a) Air temperature, -10 °C.

(b) Air temperature, -20 °C.

Figure 91 .--Aerodynamic effects of fluid 5.2 on two-dimensional model in flaps 5, sealed-slat config- uration. Data corrected for dynamic q effects.

3.2 Lx_i: ,_ , , i.K ,, 2.8 ...,. .....

."2 2.4 _.

2.0 c"

1.6 i4i(: '

....._ _i!i_ _i_!_

a) if:i=, S _!! +

1.2 _

,1=

i ,i i. _- !_,_ _ i

-I

.8 T

.4 £

0 _ --2 0 .04 .08 -.18 -.20 -.22 -.24 -.26 -.28 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0._5 E attack, aB, deg Figure 92._Aerodynamic effects of initial fluid depth of fluid 3 on two-dimensional model in flaps 5, sealed-slat configuration. Air temperature, -20 °C; data corrected for dynamic q effects.

7_ii!

J:i _7 .8 .fz

;i

i: .-3 ..+_ (5 t- .02 .06 .22 -.20 -.22 -.24 -.26 -.28 -.30 2 6 10 14 18 (D 0) o 2.8 .._1 2.4 " :: "_- '_;' :':

2.0, : i/;i_i :!',; :_

! i Z/I J,: :_!i!: 1.6 .......

1.2 :¢)(t_ il i,:;"_')i':_ ....

.8 I /!' i _ i!!I "#:J{ _

i:ti_ .18 .22 -. 18 -.20 -.22 -.24 -.26 -.28 -2 2 6 10 14 18 Body waterline angle of Pitching moment, CM,0.25E CD,SA attack, (Y-B, deg (a) Time to rotation, 20 sec.

(b) Time to rotation, 25 sec.

Figure 93.--Aerodynamic effects of time to rotation and fluid 3 on two-dimensional model in flaps 5, sealed-slat configuration. Data corrected for dynamic q effects.

4.0

_, ii!!,!i_ ¸_+-

3,6 3.2 :i, i_ ¸ !

2.8 ::17 _:i:ii_ .4.., _iiiii .-_ 2.4 tO Q)

_i _, _ _,' -fi,"! t '-i '!_i'_i

8 2.o

-i-_:_: i4 i i _ :{ i i

-n 1.6

7] 77 ,71 17 777L 7i _k _

1.2 5_

i ]!Th; : } # 7!'i :_

.8 _ -2 14 18 .04 .08 .12 .16 .20 .24 -.3 -.4 -.5 -.6 -.7 -.8 Body waterline angle of Pitching moment, CM,0.25 E Drag coefficient, CD, SA attack, a B, deg Figure 94.--Aerodynamic effects of velocity at rotation and fluid 3 on two-dimensional model in flaps 15, gapped-slat configuration. Air temperature, -20 °C; data corrected for dynamic q effects.

3.2

1::iI_-,4,'

7: l- !':I I;_ L lil:;_J J !

2.8 itil_ ! '4i ,_;, _.t _, :L ]Liil _ i , _ ,. , : _;'J 2.4 'i :!i_ }il !

-.,_ I!_ !i

d

2.0 ¢:: G) _ i !i ...... t ....

1.6 _3 i,

1.2

.=_

::i jj '

.8

r_ ! : 0")

t

i i_i'/

.4 i:_

' '"': ..... 4l:! ;i_-. i J

-2 2 6 10 14 18 •02 .06 .10 .14 .18 .22 0 -.1 -.2 -.3 -.4 -.5 Body waterline angle of Drag coefficient, CD, SA Pitching moment, CM,0.25 E attack, (_B, deg Figure 95.--Aerodynamic effects of fluid 3 on two-dimensional model in flaps 5, gapped-slats config- uration. Air temperature, -20 °C; data corrected for dynamic q effects.

2.8 2.4 ! _.E_,_,_, :i 2.0 _

:i:- i ,.4"

.../ (3 .-4- r"

._e -

O O O 'Z ! F F __ ._J 0 _ il 4 iii _:; i

-.4 i!_:k - L

18 -2 2 6 10 14 .02 .06 .10 .14 .18 .22 -. 16 -. 18 -.20 -.22 -.24 -.26 Pitching moment, CM,0.25 E Body waterline angle of Drag coefficient, CD, SA attack, (x B, deg Figure 96.--Aerodynamic effects of simulated frost and chord coverage on two-dimensional model in flaps 5, sealed-slats configuration. Ambient temperature; data corrected for dynamic q effects.

3.2 L! ¸;

2.8 -i _ !i _i_'_¸!_! _! ii

_ !ii _i ¸ !_i _i: ,_-_ _ _

_i ¸ii¸ _i_

2.4 i_

2.0

] .6 i H I| , 1.2 _: • I

.8 _i!i

7'i' I -.18 -.20 -.22 -.24 -.26 -.28 0 .04 .08 .12 .16 .20 -2 Ill 4.0

0 _ ' !_l

. : < i-rt ....

r._-Vi :_ _ [-!

3.6 ::_!

,--I IL_ " ' , °_, .

ii ;_-i i, ,!17[:. • 7_... i • :'i;= i 3,2 _

2.8 !_

.......... !: R l',_r.

2.4 _

_l-.... ii{ 777 L-j7

iiTi ........

ill: _: 1:'7 IITi _ ;H,!_t!:

1.6 t_i

_ 7_ :__7 ......._ .......

N_ 'i .... i

-'7 <,>i4

.... ' :'_ 11;; i,i ....... ;":_

18 -.4 -.3 -.5 -.6 -.7 -.8 -2 2 6 10 14

of

Body waterline angle Pitching moment, CM,0.25 E Drag coefficient, CD, SA attack, _B, deg (a) Flaps 5, sealed-slat configuration; temperature, -20 °C.

Flaps 15, gapped-slat configuration; temperature, -10 °C.

(b) Figure 97._Test technique verification for two-dimensional model with fluid 3. Data corrected for dynamic q effects.

Next: Appendix D →

Appendix D

and Wave Data

Fluid Depth

Two-dimensional Model Results

This appendix contains the results of the ultraviolet fluores-

cence photography technique. The key features of the technique

Fluids 1 to 4.--Figures 100 to 103 show the fluid depth

were as follows:

profiles for all four of the basic fluids on the two-dimensional

(1) A 0.005 percent concentration of Rhodamine 6G

model in the flaps 5, sealed-slat configuration at -20 °C. The

fluorescent dye was added to each of the fluids.

corresponding wave patterns were shown in figures 51 to 54.

(2) A 70-ram Hasselblad camera with a Kodak Wratten 2E

In figure 51 the photographs of fluid l are shown on the right

Ultraviolet barrier filter was mounted in the ceiling of the

and the corresponding fluid depth profiles are shown on the

tunnel, directly above the model. Black and white film was

left. In the photographs, increased fluorescence corresponds

used because it provides better resolution.

to increased fluid depth. In some cases it may be noticed that

The ultraviolet barrier filter blocked out the ultraviolet light

the average fluid depth in the fluid depth profile at the earliest

and admitted the fluorescent light emitted by the dye in the

time shown (usually l0 sec) appears to be significantly deeper

fluid. The brightness of the fluorescent light emitted by the

than the initial depth noted in the plot. This initial depth was

fluid increases with increasing fluid depth, since the light is

measured manually at approximately 50 percent chord before

emitted by the fluid at all depths. This brightness was calibrated

the run. This apparent discrepancy is primarily a result of the

against fluid depth using the calibration plate discussed below.

details of the fluid distribution along the chord at the time the

(3) Two 2000-W sec strobe lights with ultraviolet exciter

manual depth measurement was made. In some cases the single

filters were mounted directly above the model, one at each

50 percent chord depth measurement was not a good average

end of the span.

value for the entire chord.

(4) In order to get a continuous record of the fluid flowoff,

Figures 100(a) to (c) are larger scale versions of the three

a video camera was mounted in the tunnel ceiling above the

fluid depth profile plots shown in figure 51. Each contains

model. Video tape recordings were made for each of the fluid

an inset showing a blow-up of the region from approximately

runs.

50 to 55 percent chord. The noise level for this technique was

(5) An ELC 4000 light source with an ultraviolet exciter

estimated to be about 0.1 mm (0.004 in.). Therefore, fluid

filter was also mounted in the tunnel ceiling to provide a

waves of this amplitude or smaller are not significant.

continuous source of ultraviolet light for the video camera.

Effect of initial fluid depth.--Figures 53 and 104 show the

Figure 98 is a photograph (taken from above) of the lights

fluid depth profiles and wave patterns for fluid 3 with initial

and cameras mounted on the tunnel ceiling.

fluid depths of 0.525 and 2.0 mm (0.02 and 0.08 in.) Though

(6) Photographs were taken in synchronization with the

there are significant differences in the fluid depth profiles at

ultraviolet strobe lights every 2 sec during each run.

the earliest time shown, there is very little difference between

(7) A calibration plate with grooves of various depths was the two figures at 26 sec. This indicates that the fluid velocity filled with fluid and photographed before each run. The is somewhat proportional to the fluid depth. The outer layers calibration plate details are shown in figure 99.

of the deeper fluid flow off more quickly than those of the

shallow fluid.

(8) After the test, a scanning microdensitometer was used

to measure the optical density of the photographic negatives Gapped slat versus sealed flat.--Figures 53 and 105 show corresponding to a specified location on the model. By doing results for the flaps 5 configuration with the slat sealed and this also for the calibration plate photographic negative, the gapped, respectively. Note that the differences between the velocities at rotation and times to rotation for these two runs.

correspondence between optical density and fluid depth for

a given run could be determined. In this manner, fluid depth For the run shown in figure 53, rotation started at 22 sec. For (including waves) was determined as a function of model the run shown in figure 105, rotation started at 25 sec.

chordwise location.

However, because of a slight delay in the start of the tunnel

Since photographs were taken every 2 sec during each run, acceleration for the figure 105 case, rotation occurred at a a large number of photographs were taken for the entire test.

velocity of about 57.6 m/sec (112 keas) in both cases. The

differences between the fluid distributions for the two cases

Only key cases at certain times were analyzed on the

microdensitometer. For most cases three times were chosen

are mainly on the aft half of the model.

for analysis: (1) approximately 10 sec after the start of tunnel

Flaps 15, gapped slat versus flaps 5, sealed slat.--Figures

acceleration; (2) just before rotation; and (3) 2 to 4 sec after

106 and 103 show results for the flaps 15, gapped-slat config-

the start of rotation.

uration and the flaps 5, sealed slat configuration, respectively.

Three-dimensional Half Model Results

Although there aresome differences in speeds andtimes to

rotation forthetwocases, thegeneral indication is thatthe

The three-dimensional half model ultraviolet fluorescence

fluidflows offmore slowly forthe flaps15 configuration than

data are based on photographs of the 60- to 70-percent-span

for theflaps5 configuration.

location. This region includes the spanwise station corre-

Flaps 15 with cruise leading edge.--The results for the flaps

sponding to the airfoil used for the two-dimensional model.

15, cruise leading-edge configuration are shown in figures 107

Flaps 5, fluid 3.--Flaps 5, fluid 3 results are shown in

and 108. The tunnel acceleration and model rotation time

figures 121 to 127. Included are three runs at -20 *C and

were changed for this case in order to be representative of

one each at -10 and 0 *C.

commuter aircraft.

Flaps 5, fluid 4.--Results for flaps 5 with fluid 4 are shown

Experimental fluids.--Results for the eight experimental

in figure 132.

fluids tested are shown in figures 109 to 120. Results are shown

Flaps 15, gapped slat, fluid 3.--Results for the flaps 15, for 0 *C and for -20 *C for fluids 2.1, 3.1, 4.1, and 5.1.

gapped-slat configuration are shown in figure 129. The

Results are shown for only -20 °C for fluids 2.2, 3.2, 4.2, secondary wave at t = 22 sec is very evident.

and 5.2.

9o

ORIGINAL _,'_AG E

_LACK AND WHITE pH_JI'OGRAPh

70 mm Hasse!brad camera

I

Figure 98.--Equipment setup for ultraviolet photographic technique.

16 grooves, depth = 0.025- to 0.406-cm by 0.025-cm increments 0.01-in. to 0.16-in.; by 0.01-in. increments --/ /-- Aluminum I plate (3/8 in.)

I / 0.32 cm I I _0.95 cm 4'1"_- (1/8 in.)

25.4 cm (10 in.)

._] 25.4 cm (10 in.)

___I_

2.54 cm I UUU' " " '_-

(1 in.)

Figure 99.--Calibration plate.

+-.+ +-q pd+ +,_.

t+-+t F_

"i

-! I hh,l

+ ++I iii+II

4+HI-Htt

_t lit il

i IINt._t

,I,P:_'II+, I

::i+! +-+FI!

....+-__ _ .... i_

i

.7 .9 1.0 (a) Elapsed time, 10 sec; airspeed, 24.2 m/sec (47 keas); O+w= O; h = 0.166 mm.

(b) Elapsed time, 24 sec; airspeed, 61.2 m/sec (119 keas); <x w = --0.1°; h = 0.451 mm.

Figure 100.--Fluid 1 depth profiles and detail roughness inset for two-dimensional model in flaps 5 conliguration. Initial depth 0.750 mm; temperature, -20 °C.

(See fig. 51 for wave patterns.)

,: i i

i r litI1_, : i_ i ii ii i i+ ii. -i

.,iii !!._

* t i , i

de,h '_- _:/ :_! _ t I,!!tlI,N_:. t

_,o _ _,_ _,,3o_ 3,0 _-t_tl,tltllll_lHi r i |1 I J

_L Distance from leadlng edge _m _llllllll_lilll-_' : " ' '

i (approximately _O_oh_ i _ i_,l_llll_llllllilll_ _J : 1 I1_-!

I, i ', I "i!Ti jj !tl

! i,I I ti l i::;:t_ii ti_!U_Jtl:t'!!ti-i ilt/_L_

!t-lt_l _,--_t, i _ _Jl_l_!t_t it-_lt I _/_1/f

i} It f i } :t ! ]I ti } iill_!.ltf,:c I!t ! t!llll _Y I]{

It I_-,-:--_-:l_,_:,{:,I/_ILll _:t J_t,d} Ill

0 .1 .2 .3 .4 .5 .6 .7 .8 .9 1.0 Chord location, x/c (a) Elapsed time, 10 sec; airspeed, 25.2 m/sec (49 keas); ew - O; h - 0.226 mm.

(b) Elapsed time, 22 sec; airspeed, 57.6 m/sec (112 keas); (_w = -0.1°; h = 0.864 mm.

Figure 101 .--Fluid 2 depth profiles and detail roughness inset for two-dimensional model in flaps 5 configuration. Initial depth, 1.0 mm; temperature, -20 °C. (See fig. 52 for wave patterns.)

-+4 llt_lllll_l_it

_j_] i]! !o,):

; 2.e= E -_

t- ..... _- _ ....

_Ruid 1 8! i -_t_, • ..... -_i-! - __+_ _+_ b- mm 1.01 ! " I, '_;_] -

+_ ..... I[ t '

I .... i i

+ 270 278 286 294 302 310

_-__ _- _1 l- )

Distance from leadingedge,mm (approximately 50_ chord) I • -i" : - ; T-_ ...........

3 1

d--!-h-a_...i._j._.[ ..i.L

..... i i , ! .... I-.... [ i

Ll_4_, !

_ i --- F- =

l

I

-[--- b i -tl; -Fill....

!

' ' ¢-_-T

,,, li

•'-_ ¢-_-_4J,26 l _; _i--Il i l -l-_--..[d--f-I--!--

-;_F,,Ot.81 ' .... _.... .i._i

+' I ill

-t i ¸

_<_", I ii I [ HI

" i P m m 1 . O t . . . . . . . . . . i _ - r _

I

.... 1- _ i I '270 278 286 294 302 310t I E E -4

•p-_- t 1

.__ 3 .÷ ....

, 1 I _ _ .....

I J-

! i_i i , _i'

-_..--f d-. +-

ji i ....... ,..,..; I

-i-, --_- .... ,i-s=iii .....

-..s-, ........ 4--lift:. I

..... i .....

.÷ _ r'4l._.d_J #.-

: i ', : I L; I : I] -., ......... J,.-,-4.-+--1--.+--_--_-4 _-.-;-..--..--,-.4--+...4-7 d-,--, _-:---_---.T-- -- -_.--+ d- _'- 26½ '_:-, _ = T ' ' ' I ; ' i( ,' d hR""_...,_ 1.0" 7].-_.¢_]_'_4 _ ''_1, I-t]_ -_ ,_]'_'l,_'] __i ,.... +i ,_[ ......... , ,Li' ............... ,_; _t'1 +, ,...... llilt'- , -_ _ '_- i i J t t J ; i , / r f ', / J

2 i t ti--4-i t !t i t-t--i-

-1- 270 278 286 294 302 310 +- i i , i / _ r _ 7 i _

-+ o,,,,a,_,.=.,,ea<,,_.,_..-.',', _l-t-f-+ '-_- _1 I r i-t _!

4" T (approximately S0o_ chord) , ! / / : . [ 1 i t I I [ t [ I I I l I ! i I I _l! _ll, _,ll l;l_Y, ! i ' _ I ', : ; ! _ j ! " _ { l { [

,- t ,-I r-_ l-.--t.k--t t _ t-i I _.t-:-f---r i-! J-r, l_-t ,t-r-f-, t-_

/ ! i / i I i i : I i ,i , I i i I i , , , = , i r r _ , i i

_i_--.-1-_ d --.-l.+-"d.-4 t_14--_---i ,t.,__-

' i [ I t I i ,I !. ' ; ,

li i t , , , ,,i I i

i " , : I I I I ! ' '1 ' r ;

r

0 .1 .2 .3 .4 .5 .6 .7 .8 .9 1.0 Chord location, x/c (a) Elapsed time, 10 sac; airspeed, 25.2 m/sac (49 keas); o= w - 0.1°; h = 0.15 mm.

(b) Elapsed time, 22 sec; airspeed, 57.6 m/sac (112 keas); _,w= 0.1°; h = 0.340 mm.

Figure 102._Fluid 3 depth profiles and detail roughness inset for two-dimensional model in flaps 5 configuration. Initial depth, 0.525 mm; temperature, -20 °C. (See fig. 53 for wave patterns.)

I ; i ; _ i = I , I ' _ = i I'

--tU r _ :__ ........ 1--_ L_ M .............. _J........ ,_--_! :- ,(a)'- _-

! ! / i --k 2.6 [; I ..... _--L_ -_=-! t i ] I i ! i , _L_ _ _--- . . _ [ i ; ' , t -!- ' = J ' " _- I _L _., _ i $ i .

, depth _ - _ = _ _ _ ; ' ' mm 1 i , ' t, = --r 1 , , "- " i ! !-" 270 278 286 294 302 3101 _ i . .L-r.j ! i !

i i t } Oist .... from,..,ng.._.. _ i ,d, t _t ! _ I

4' .._ _ _. _- (approximately 50_ chord) t ._._L_ t ! I i- -T-- I ' I 1"- "- + ! .... 4- -'_ i : : I I j _! '_._iI ' I ; I i : [ r t' _ t ' ..... -....... , , , -;-y,

} _!_._J.L__ LI i LilJ I L.L_i L',[ ! L

I!i 261 !II: ; ! ]

I-r

_,,_,,. l!i] : I

I _ti .z ' '

I

E 270 278 286 294 302 310 Distance from leading edge, mm E

Iltt l :t

: : i

(approximately 50% chord) i Iltt4t -I

-4 J_

- r:lT i ¸ I i

i H_

i _tt I: E 2 i ....

i . r L ,_14_,.

tt f t

.i, I i

"'.'i[TJ i i ! I .... '" iT i- -ft

I I I_ _.-._LL.I_J .L_-.LJ.J._L.L_ l....][ 2.6 _. ]]:J i]: !L .kL ]-iJ-LI i- 1-- -I- F T I ,!J!l I i ! ! ii I Iluid 1.8 J t I : ] i p _

.... _m _.o I! i_ Ii_ .... _'--[--

i ._ _t--u"-, :t 14

F--4- .... Distance from leading edge, mm J-b

L l-

4 ; (epproxlmately 50_ chord) il i 270 _7__ _, _o_ 310,_ !--: _ .L l kH L._ _ } L_ , , _--_- 7 -T- -r T _y _

t r- F .... I I rl [-

l_i_l

4--I -i--

.,4' , '

;- F-i-FTT[--Z2:i.l.a::IlllIil

i _-!

.1 .2 .3 .4 .5 .6 .7 Chord location, x/c (a) Elapsed time, 10 sec; airspeed, 24.7 m/sec (48 keas); O_w- O; h = 0.479 mm.

(b) Elapsed time, 22 sec; airspeed, 56.5 m/sec (110 keas); _w = -0.1°; h - 0.288 mm.

Figure 103.--Fluid 4 depth profiles and detail roughness inset for Iwo-dimensional model in flaps 5 configuration. Initial depth, 0.810 mm; temperature, -20 °C. (See fig. 54 for wave patterns.)

ORIGINAL PAGE

BLACK AND WHITE PHOTOGRAPh'

Fluid depth profiles Fluid wave patterns

(TE) (LE) (LE)

(TE>

(a)

T-; T i ;_-I-_---I-I-C---C -_

E E "0 =, (b) 7 I- '" ; T i r _ _ T ......... :-i

i I !i ! i i ¸

L

! ' ' i

: : ! i i, !

t : : ] i i i : I

L_' ' i I _ _ '

(c)

0 50 100 Chord location, percent (a) Elapsed time, 12 sec; airspeed, 30.3 m/sec (59 keas); ew = -0"2° (b) Elapsed time, 22 sec; airspeed, 57.1 m/sec (111 keas); a w = -0.3 °.

Figure 104.--Fluid 3 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration. Initial depth, 2.0 mm; temperature, -20 °C; run 327.

ORIGINAL P;_GE

BLACK AND WHITE. PHOTOGRAPi-(

Fluid depth profiles Fluid wave patterns

(TE) (LE) (LE) (TE) 7 " ' - i : J i ..... , ' ' .... i _ ' i ........

..... i I : ! i ........... i

(a)

i:_:! ! !ii _ E i E t- i .... I '_: :I_ "O i i _ ,I : ,,!! _:1 I E.

, i i , , (b)

(c)

0 50 1O0 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 18.0 m/sec (35 keas); a w ffi 0 °.

(b) Elapsed time, 24 sec; airspeed, 54.5 m/sec (106 keas); a w = 0 °.

Figure 105.--Fluid 3 depth profiles and wave patterns for two-dimensional model in flaps 5, gapped slat configuration• Initial depth, 0.475 mm; temperature, -20 °C; run 458.

9"7

O,,luIHAL PAGE

BLACK AND WHITE PHOTOGRAPh

Fluid wa_ patterns

(LE) (LE) (TE) (a) (b)

! i ' ,t ! ' _ ' :-'

(c)

50 1O0 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 25.2 m/sec (49 keas); ew = 0°' (b) Elapsed time, 20 sec; airspeed, 51.4 m/sec (100 keas); ew = -0"1° (c) Elapsed time, 22 sec; airspeed, 56.5 m/sec (110 keas); _w = 4'9°• Figure 106.--Fluid 3 depth profiles and wave patterns for two-dimensional model in flaps 15, gapped slat configuration. Initial depth, 0.60 ram; temperature, -20 °C; run 422.

_ ;,-,,,._I;'.JAL PAGE

BI.J'_.CK _:;J";.OWHITE PHOTOGRAPH

Fluid depth profiles Fluid wave patterns

(LE) (TE) (LE) (TE)

I

, I (a) E E (b)

(c)

50 100 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 22.6 m/sec (44 keas); aw= -0.1 °, (b) Elapsed time, 16 sec; airspeed, 37.5 m/sec (73 keas); ew = 1.0 °, (c) Elapsed time, 18 sec; airspeed, 42.1 m/sec (82 keas); a w = 7.3 °.

Figure 107.--Fluid 3 depth profiles and wave patterns for two-dimensional model in flaps 15, cruise leading edge configuration. Initial depth, 0.50 mm; temperature, -20 °C; run 442.

q_ 24E!!_l!!i!i!!i!l!P_i -!

____L. L_i--I 1i i L L l _JiI r.i!

l-_depth, _| !l_r_ i_ :_ ' __ ; ! O[ i ,:, ,,i _ _ : --I 270 278 286 294 302 310 t _- Distance from leading edge, mm !

( apprOximalely 50°_ ch°rd) _ ' i i i 1 i_-' ,

2, • If I >

Fluid 1.6 t j T deplh, "

E

E Distance from leading doge, mm [

- 4

(3.

e) --I i . ' (app!°x'_'_ate'Y 50q_ ch°rO' ! l. !- 11 "e 3 "5 ,5- 0 .1 .2 .3 .4 .5 .6 .7 .8 .9 1.0 Chord location, x/c (a) Elapsed time, 10 sec; airspeed, 22.6 m/sec (44 keas); ew = 0.1 °.

(b) Elapsed time, 16 sec; airspeed, 37.5 m/sec (73 keas); ew = 1.0% (c) Elapsed time, 18 sec; airspeed, 42.1 m/sec (82 keas); e_ w = 7.3 °.

Figure 108.--Fluid 3 depth profiles and detail roughness inset for two-dimensional model in flaps 15, cruise leading edge configuration. Initial depth, 0.50 mm; temperature, -20 °C.

BLACK AND Wi..{JT[[ PHOTOGRAPH

Fluid wave patterns

Fluid depth profiles

(TE) (LE) (LE) (TE)

_a)

I . , ; .... i ....

E E

=-

O :3 LL

(b)

o 7 ¸ r ...... T- -_ -- 7_" - _ _ .... _-: --_

(c)

0 50 100 Chord location, percent (a) Elapsed time, 12 sec; airspeed, 27.2 m/sec (53 keas); ew = 0.

(b) Elapsed time, 24 sec; airspeed, 57.6 m/sec (112 keas); "w = 0.

Figure 109.--Fluid 2.1 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.500 ram; temperature, 0 °C; run 520.

Fluid wave patterns

(TE) (LE) (a)

E

"C} _.= tl (b)

• i;!i_-?! _

t ! : ! ! _ I

i-I !--

I ! ! I i , -F -:" !-1 i _'_,

(c)

50 100 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 25.6 m/sec (4g keas); _w = -0"1°' (b) Elapsed time, 24 sec; airspeed, 62.2 m/sec (121 keas); a w = -0.2 °.

(c) Elapsed time, 26 sec; airspeed, 66.8 m/see (130 keas); (_w = 34°- Figure 1lO.--Fluid 2.1 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.55 ram; temperature, -20 °C; run 488.

Fluid depth profiles Fluid wave patterns

(LE) (TE) (LE) (TE) I I (a) E E

=.-

t-., "0 ,'T (b) i

(c)

0 50 100 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 25.2 m/sec (49 keas); a w = -0.2 °.

(b) Elapsed time, 24 sec; airspeed, 61.7 m/sec (120 keas); a w = -03 °.

(c) Elapsed time, 28 sec; airspeed, 69.9 m/sec (136 keas); a w = 9.3°• Figure 111.--Fluid 2.2 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.525 ram; temperature, -20 °C; run 490.

ORIGI N,'-_L PAGE

8LACK AND WHITE PHOTOGRAP_

Fluid wave patterns

Fluid depth profiles

(TE) (LE) (LE) (TE) ..... : .... :--T ......... ]-_- ----T-]-:-I

::!il I i,/

i i ::i! i I_ _: :/

' i!i!l_i i' t:!_ /

: : i " I: ! I / , ' i _ , t .... I , , ,i , _i ' '!.11!1i !

_ :' !' t ! ] ! ! Ii' [ :]i' t ' : I i i i : _ ! i : ] : (a) 7 ....................

E E Q.

_.o I.L (b)

(c)

50 1O0 Chord location, percent (a) Elapsed time, 12 sec; airspeed, 27.2 m/sec (53 keas); (z w = -0.8 °.

(b) Elapsed time, 24 sec; airspeed, 57.6 m/see (112 keas); et w = -0.8 °.

Figure 112.--Fluid 3.1 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.500 mm; temperature, 0 °C; run 519.

f , T', _ mlr,_ p

,J,-,,{;,_x,*,_ PAGE

BLACK AND WHITE. PHOTOGRAPH

Fluid depth profiles

Fluid wave patterns

(LE) (TE) (LE) (TE) [ ; .... i._. ; J , ! .... I (a) (b)

(c)

0 50 IO0 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 23.6 m/see (46 keas); _w = "0'4° (b) Elapsed time, 24 sec; airspeed, 60.1 m/sec (117 keas); _w = -0"4°' (c) Elapsed time, 26 sec; airspeed, 64.8 m/sec (126 keas); a w = 1.9 °.

Figure 113.--Fluid 3.1 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.530 mm; temperature, -20 °C; run 492.

ORIGIiqAL PAGE

BLACK AND WHITE PHOTOGRAPH

Fluid depth profiles Fluid wave patterns

(LE) (TE) (LE) (TE)

(a)

o . _ _T!_:_

= ___ i :_tt -lit!t

_ ilii

(b)

(c)

50 1O0 Chord location, percent (a) Elapsed time, 10 see; airspeed, 24.2 m/sec (47 keas); a w = -0.2 °.

(b) Elapsed time, 24 se¢; airspeed, 59.6 m/see (116 keas); a w ffi -0.3 °.

Figure 114.--Fluid 3.2 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.500 mm; temperature, -20 °C; run 493.

8t..ACK ArID '¢,/Hii2 P_-t0Td_c_RA_-:t-i

Fluid depth profiles Fluid wave patterns

(TE) (LE) (TE) (LE) , : , , _ : - : , : J, ' : .... i .... ) (a) 7 .... : - - _........ 7 ......

E E

d

¢, ......... j "O i ..... I -1 IT .... i (b) 7 _ ; .... _ ; "

(c)

0 50 100 Chord location, percent (a) Elapsed time, 12 sec; airspeed, 14.9 m/sec (29 keas); a w = 0.3 °.

(b) Elapsed time, 24 sec; airspeed, 44.7 m/sec (87 keas); a w = 02 °.

Figure 115.--Fluid 4.1 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.425 mm; temperature, 0 °C; run 518.

ORIGINAL ]-',_L

BLACK AND WHJTE PHOTOGRAPh

Fluid depth profiles Fluid wave patterns

(LE) (TE) (LE) (TE) ] : : ...... ,

(a)

E E

=-

"O ,'T i

(b)

(c)

0 50 O0 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 24.2 m/sec (47 keats); a w = --0,3 °.

(b) Elapsed time, 24 sec; airspeed, 61.7 m/sec (120 keas); _w = -0.4 °.

(c) Elapsed time, 26 sec; airspeed, 66.8 m/sec (130 keas); _w = 4'2°" Figure 116.--Fluid 4.1 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.450 ram; temperature, -20 °C; run 481.

t_i;;G!i,_/',,L TV.,G tI

I__bACK ./-_,ND WHITE. phOTOGRAPH

Fluid depth profiles

Fluid wave patterns

(LE) (LE) (TE) 7 q..............

f!TTr : (a) !

I I I

E 1: r

E L

f-- i

"10 -- [I i • i I _t ii - t

.k

(b) 7 --i .... , .........

.... _ ........ d --

I --- i i -

-,4 -- _ I....... I

(c)

0 50 100 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 25.7 m/see (50 keas); aw= -0.1 °.

(b) Elapsed time, 24 sec; airspeed, 62.7 m/sec (:122 keas); ¢x w - -0.1 °.

Figure 117.--Fluid 4.2 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

InitJai depth, 0.475 mm; temperature, -20 °C; run 482.

_LACK AND WHITE PHOTOGRAPH

Fluid depth profiles Fluid wave patterns (LE) (TE) (TE)

(a)

E E

g

"O LL

(b)

(c)

0 50 1 O0 Chord location, percent (a) Elapsed time, 12 sec; airspeed, 27.8 m/sec (54 keas); a w = 0.1 °.

(b) Elapsed time, 24 sec; airspeed, 57.6 m/sec (112 keas); aw= 0.1 °.

Figure 118.--Fluid 5.1 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.475 ram; temperature, 0 °C; run 516.

11o

_..ACK AND WHITE PHO-;O,GR,c,p_

Fluid depth profiles Fluid wave patterns

(LE) (TE) (LE) (TE)

1!i i lli_i_ii!il!ii[_!ii_ii_i

': - _ i -l-i -!i _ '

(a)

E E

d

t_ "0 v.

(b) i , ! , :. L/:[i;ilAllll. [ i,

(c)

0 50 100 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 24.2 m/sec (47 keas); a w = 0.3 °.

(b) Elapsed time, 24 sec; airspeed, 61.7 m/sec (120 keas); aw = 02° (c) Elapsed time, 26 sec; airspeed, 66.8 m/sec (130 keas); _w = 44° Figure 119.--Fluid 5.1 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.500 ram; temperature, -20 °C; run 485.

Ill ._.,- . i-; ¸ o

. ,,;.,_A,. PAGE

Fluid depth profiles Fluid wave patterns

(LE) (TE) (LE) (TE)

::,.:l:p I ,:[

E (a) E Q.

I.L (b) 0 50 1 O0 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 24.2 m/sec (47 keas); a w = 0 °.

(b) Elapsed time, 24 sec; airspeed, 61.7 m/sec (120 keas); ew = O. 1 °.

Figure 120.--Fluid 5.2 depth profiles and wave patterns for two-dimensional model in flaps 5 configuration.

Initial depth, 0.500 mm; temperature, -20 °C; run 486.

Fluid depth profiles

Fluid wave patterns

(LE) (TE) (LE) (TE)

(a)

7 T E E !

t- iT (b)

(c)

0 50 1O0 Chord location, percent (a) Elapsed time, 9 sec; airspeed, 25.7 m/sec (50 keas); _B = -0.1 °.

(b) Elapsed time, 21 sec; airspeed, 59.1 m/sec (115 keas); eB = -0"1°' (c) Elapsed time, 24 sec; airspeed, 66.8 m/sec (130 keas); eB = 4-4°- Figure 121 .--Fluid 3 depth profiles and wave patterns for three-dimensional half model in flaps 5 configuration Initial depth, 0.475 mm; temperature, -20 °C; run 149.

I _ I_.L[ i i_J E I'= .....

--i- ?

' --1 ¸` --i. : ..... ; i i..... i

I V

i 270 ' 278- 286 ' 2cJ4_ 302 3102 E Distance from leldlng edge, mm - E _-- - (approximately 500/0 chord) _- -4 J=

: i

! • ' .q. : "0 _ i i-i-If- J : .g_ 3 LL : T ; i -_i _-__-_'_'=r ' _ _-= "-_ :.,' ....... --_-..} -__ _1_-i--}t ....

' : __ : _ i,i .... i ..... _ ............

• , .... " , r '{- _ ! ] , . 24.'.4_LJ__J :3 4--- _ J _

-_(c) i

-.,.J-.i. I } i I i J i..J.J I ! :1-'_4.[ 4 [ .

depth i :;-T" _ : ' i Ill J] .... ' i r _iI....

27027_ 2_ 2_, _o2 _o. I: I _ : i i

- r, Dl=tance Irorn leading edge, mm .; I I : (approxmmtely 50o_ chord) i .......

i r_i , , 2.

.1 .2 .3 .4 .5 .6 .7 .8 .9 1.0 Chord location, x/c (a) Elapsed time, 9 sec; airspeed, 25.7 m/sec (50 keas); "B = -0"1°; h = 0,238 mm.

(b} Elapsed time, 21 sec; airspeed, 59.1 m/sec (115 keasJ; a B = --0.1°; h = 0.422 mm.

Figure 122.--Fluid 3 depth profiles and detail roughness inset for two-dimensional model in flaps 5 configuration. Initial depth, 0.475 mr'a; temperature, -20 °C.

O_,_INAL PAGE

P, LAC,_ AND WHI"E PHOTOGRAPH

Fluid depth profiles Fluid wave patterns (LE) (TE) (LE) (TE) E t-t I i

-ii

t [ !

0 ,2 (a)

!:i: I:I

E i_-ii

E t-_+-

=S

im -1o

I:T- i-i

it ,

Jilt-_

I J_ _-!

(b> -i .... i [

i ÷_ LL_ !

(c) 50 100 Chord location, percent (a) Elapsed time, 12 sec; airspeed, 35.5 m/sec (69 keas); _B = 01° (b) Elapsed time, 20 sec; airspeed, 56.5 m/sec (110 keas); eB = 0-1° (c) Elapsed time, 24 sec; airspeed, 673 m/sec (131 keas); _B = 81° Figure 123.--Fluid 3 depth profiles and wave patterns for three-dimensional half model in flaps 5 configuration.

Initial depth, 0.480 ram; temperature, -20 °C; run 230.

_"":IAL pAGE

_}:L_,-L;_, WqD WHIT_ PHOTOGRAPH

Fluid wave patterns

Fluid depth profiles

(LE) (TE) (LE) (TE) : , : [ . ....

/ [ ' ' ' /

I

.... i IlL

i: !! :'/t!i I

(a) 7 [? - : :-[ 7-' _,--: i. 1 E E .E CI.

"lD U- L " i i : I _ ; (b) ! , i I " ' i ,

(c)

._--i',-_ __': ....

0 50 1O0 Chord location, percent (a) Elapsed time, 12 see; airspeed, 36.5 m/see (71 keas); ot B = O.

(b) Elapsed time, 22 sec; airspeed, 62.7 m/sec (122 keas); a B = O.

(c) Elapsed time, 24 sec; airspeed, 67.4 m/see (131 keas); a B = 59 °, Figure 124.--Fluid 3 depth profiles and wave patterns for three-dimensional half model in flaps 5 configuration Initial depth, 0.450 mm; temperature, -20 °(i; run 232.

• . . - .

Fluid depth profiles Fluid wave patterns

(TE) (LE) (TE) (LE) 7, ca)

E !

d

Li_

(b)

(c)

o 50 10o Chord location, percent (a) Elapsed time, 12 sec; airspeed, 35.0 m/sec (68 keas); a B = -02 °.

(b) Elapsed time, 22 sec; airspeed, 61.2 m/sec (119 keas); a B = 1.5*.

Figure 125.--Fluid 3 depth profiles and wave patterns for three-dimensional half model in flaps 5 configuration.

Initial depth, 0.425 ram; temperalure, -10 °C; run 180.

5 ¸ 4, .1 .2 .3 .4 .5 .6 .7 .8 .9 Chord location, x/c (a) Elapsed time, 12 sec; airspeed, 35.0 m/sec (68 keas); =B" -0.2°- (b) Elapsed time, 22 sec; airspeed, 61.2 m/sec (119 keas); _B - 1.5 °.

Figure 126.--Fluid 3 depth profiles and detail roughness Inset for three-dimensional half model in flaps 5 configuration. Initial depth, 0.425 ram; temperature, -10 °C.

ORIGINAL F_A,G E

BL,_CK AND WHITE P_tOTOGRAD_

Fluid depth profiles Fluid wave patterns

(LE) (TE) (LE) (TE) • , I i , i ! L i i i _ • i _a) E :!rii',_!

=-

= ii= ......... : "10 I,L i , i i .' _J i i : , i I _ i ; _

, ' , , 3 , ,t'Y_Tv • (b)

ii: ;_! !iri:-i!

_::I'I_; !:! _ .... i ; : , ! i ; i ,; • I _ _ , = i .... i , : _ _ _ . : ,_i i i i-_ ; , ! _I

(c)

0 50 1oo Chord location, percent (a) Elapsed time, 12 sec; airspeed, 33.4 m/sec (65 keas); a B = 0.1 °.

(b) Elapsed time, 21 sec; airspeed, 56.5 m/sec (110 keas); _B = 01° (c) Elapsed time, 24 sec; airspeed, 69.3 m/sec (125 keas); _t B = 9.4 °.

Figure 127.--Fluid 3 depth profiles and wave patterns for three-dimensional half model in flaps 5 configuration.

Initial depth, 0.425 ram; temperature, 0 °C; run 172.

..,,_,, L_ t, _IP,L

_LACK AND WHITE priOTQGRAP_

Fluid depth profiles Fluid wave patterns

(LE) (TE) (LE) (TE)

¢

(a) E E o_ "0 ii

CbJ

(c)

50 1 O0 Chord location, percent (a) Elapsed time, 9 sec; airspeed, 27.2 m/sec (53 keas); _w = O.

(b) Elapsed time, 21 sec; airspeed, 60.1 m/sec (117 keas); _w = O.

(c) Elapsed time, 24 see; airspeed, 67.8 m/see (1`32 keas); _w = 70° Figure 128.--Fluid 4 depth profiles and wave patterns for three-dimensional half model in flaps 5 configuration.

Initial depth, 0..375 mm; temperature, -20 °C; run 155.

Fluid depth profiles Fluid wave patterns (LE) (TE) (LE) (TE) (a) E E IT [b) (c) 0 50 1O0 Chord location, percent (a) Elapsed time, 10 sec; airspeed, 29.3 m/sec (57 keas); _w = O.

(b) Elapsed time, 20 sec; airspeed, 56.5 m/sec (110 keas); _w = 01° (c) Elapsed time, 22 sec; airspeed, 61.7 m/sec (120 keas); _x w = 6.1 °.

Figure 129.--Fluid 3 depth profiles and wave patterns for three-dimensional half model in flaps 15, gapped slat configuration. Initial depth, 0.500 mm; temperature, -20 "C; run 205.

Next: Appendix E →

Appendix E

and Data Corrections

Data Repeatability, Tunnel Calibration, static source was used as the reference static pressure for the Data repeatability for both the two-dimensional model and three-dimensional half model. The location of this static source the three-dimensional half model is summarized in this is shown in figure 133. To determine the difference between appendix. Also included is the calibration of the wind tunnel the reference static and the static pressure at the model location, to account for the difference between the static pressure at the a temporary static port was located at the center of the measurement station and that at the model location. Finally, turntable. The tunnel was then accelerated (model out) from the corrections applied to the raw wind tunnel data are 0 to 77.1 m/see (0 to 150 keas), and the static pressure was discussed.

measured at both locations as a function of tunnel q. The difference between the static pressure measured at the model Data Repeatability location and that measured at the reference location at a given Three-dimensional half model lift repeatability.--The q was used in during data reduction to correct the measured repeatability of the fully corrected three-dimensional half reference static pressure.

model lift coefficient is shown in figure 130. Data are shown Two-dimensional model.--For the two-dimensional model, for fluid 3 and for the dry wing at an angle of attack of 7*, the tunnel was calibrated with both of the splitter walls installed at maximum lift and - 10 *C. For the three cases with fluid (model out). The standard IRT reference static was not used 3 on the wing, the coefficient of variation is 2.1 percent at for this model because of the proximity of the leading edge 7 ° and 1.3 percent at maximum lift. The repeatability is of the left splitter wall to the IRT static source. There was some concern that the effect of the splitter wall on the reference significantly better for the dry wing. At 7* the dry wing coefficient of variation is 1.0 percent, and at maximum lift static measurement would vary as a function of the model angle it is 0.9 percent. The dry wing data for a given temperature of attack because of the changing location of the splitter wall were averaged to determine the baseline value to which the stagnation line. Therefore, the reference static source for the two-dimensional model was located 0.9 m (3 ft) from the data with fluid at that temperature would be compared with determine the fluid effects.

leading edge of the right splitter wall (fig. 134). This location Two-dimensional model lift repeatabUity.--The two- was chosen as a result of a potential flow panel method dimensional model fully corrected lift coefficient repeatability (program A502) analysis of the model pressure field and the is shown in figure 131 for an angle of attack of 8*. All the splitter wall bullnose, or leading edge, pressure peak. As data shown are for a temperature of -20 *C. The coefficient shown in figure 134, the location chosen was aft of the bullnose of variation for the dry baseline data is 0.9 percent. Only a pressure peak about 0.9 m (3 ft) above the tunnel floor, which minimized the effect of the model. The tunnel calibration was, single repeat run was made for fluids 1, 2, and 4, and two repeat runs were made for fluid 3. The repeatability of the again, carried out by accelerating the tunnel (model out) from fluid data is reasonably good. As was done with the three- 77.1 m/see (0 to 150 keas) and measuring the static pressure dimensional half model, the dry wing data for a given at the model location and at the reference static port as a temperature were averaged to determine the baseline value to function of tunnel q. The difference between these two which the data with fluid at that temperature would be pressures was then used in the subsequent data analysis to compared to determine the fluid effects.

adjust the measured reference static to the model location as Figure 132 shows the repeatability of the fully corrected two- a function of q.

dimensional model maximum lift coefficient at a temperature of -20 *C. For the dry baseline data, the coefficient of Standard Data Corrections variation is 1.2 percent. The repeatability of the fluid data is The following corrections were applied to the raw balance not as good as it was at an angle of attack of 8".

data for both the two-dimensional model and the three- dimensional half model: (1) balance interactions, (2) temper- Tunnel Calibration ature corrections, (3) weight tare, and (4) balance deflections.

Additional standard corrections for solid blockage, wake The purpose of the tunnel calibration was to determine the blockage, and wall interference were applied to the tunnel difference in static pressure between the measurement station parameters and data coefficients for both models. The wall and the model location with the splitter wall(s) installed.

interference corrections were not applied to the three-dimensional Three-dimensional half model.--For the three-dimensional half-model data when the ground plane was installed because half model, the tunnel was calibrated with only the right splitter the purpose of ground plane tests was to evaluate the constraint wall installed. Separate calibrations were made with and to the downwash.

without the ground plane installed. The standard IRT reference Nonstandard Data Corrections the dry and with fluid runs) were (1) Fluid 1, T= -10 *C, flaps 5, sealed slat In addition to the standard data corrections, data from both (2) Fluid 3, T = 0 *C, flaps 5, sealed slat the two-dimensional model and the three-dimensional half- (3) Fluid 4, T= -5 *C, flaps 5, sealed slat model were corrected to account for effects specific to this test.

(4) Fluid 4, T = -10 *C, flaps 5, sealed slat Initial balance offset correction--three-dimensional half (5) Fluid 4, T = -5 *C, flaps 15, gapped slat model.--For five cases on the three-dimensional half model, Dynamic q effects correction--two-dimensional model.- an initial balance offset was large enough to affect the lift An additional correction was made to the two-dimensional coefficient at the post rotation conditions. A negative initial model data for dynamic q effects. The dynamic q effect refers balance offset is indicated by increasing CN with increasing to a dependence of the lift coefficient on q (or run time, since q, and a positive initial offset is indicated by decreasing CN q versus run time was constant from run to run), as shown with increasing q, since, except for a very small Reynolds in figure 135 for several runs. Notice that before rotation, cl number effect, CN should be approximately constant with q.

varies with run time (q). From 8 sec until rotation ct is Therefore, a correction was applied to the normal force at all decreasing. Also notice that Cl,ma x decreases from run to run q to make CN at q = 20 equal to CN at q = 40. These two as the run time at Ct.r_x increases.

values of q were chosen based on the following considerations: The cause of the dynamic q effect is not known. However, (1) They are high enough to be above the very low q region it may be an indication that there is an effect of the model where small changes in normal force can have a large effect on the static pressure at the reference location, and that this on CN; (2) the two values are widely spaced; and (3) both effect varies with q.

values are before rotation. The correction was computed as Since the time to rotation did vary somewhat from run to follows: run throughout the course of the test, it was necessary to make a correction to account for the dynamic q effect. The correction CN2O + DN/ (20Sref) = (CN40 + DN/(4OSref) used is based on the data shown in figure 136 from run 524.

In that run the angle of attack was kept constant at 8.1. Thus, DN = (CN40 -- Cmo)Sref/(1/20 - 1/40) any change of ct with time is due to the dynamic q effect. The first step in correcting each run consisted of adjusting the run DCL = DN COS c_B/(qSref) time corresponding to a given angle of attack to a constant value for all runs. The lift at that angle of attack was then This correction was computed for all angles of attack. The adjusted by the difference in lift for run 524 between the five cases that were corrected for initial balance offset (both adjusted run time and the unadjusted run time.

2.0 -- _ Dry • C'L = 1.643 With fluid • _ = 0.0148 • CL = 1.506 • (_ = 0.0193 • Coeff. of var. = 0.9% 1.327

• _., =

• CL = 1.239 • _ = 0.0131 • Coeff. of vat. = 1.3% !

-- • c = 0.0264 1.5 • Coeff. of var. = 1.0% • Coeff. of var. = 2.1% ..J o :,i!

¢J "O 1.0 o .:::: ::::: : ::: :::

...................... I :1

::: : : :::: : ._1 .5 : ::: :

!!

: : i :: : :: ::_ .::: I ::: 1 180 241 246 180 241 246 111 242 178 243 249 111 242 178 243 249 Run (a) At _B = 7°.

(b) At CL, max.

Figure 130.--Lift repeatability for three-dimensional half model in flap 5, sealed slat configuration with ground plane in. Fluid 3; temperature, -10 °C.

2.2 m ,_ 2.7 -- _ _).__......_baseline E G" 2.6 2.1 _ _ Dry baseline G" E qO 2.0 __ _'=" _ Fluid 1 _._ _.

2.5 <>, Fluid 4 O _E

Fluid 1 41- 8

,-, 2.4 __ ,_f Fluid 3 O 1.9 --_muidv ,, E .J Fluid 2 .-.------K> .---,-'0 1.8 _ 2.3

<>

I I I

1.7 I _ 2.2 300 350 400 450 500 300 350 400 450 500 Run number Run number Figure 131 .--Lift repeatability for two-dimensional model in flaps 5, Figure 132.--Lift repeatability at maximum lift for two-dimensional model in flaps 5, sealed-slat configuration. TemperatuCe, -20 °C; sealed-slat configuration. Temperature, -20 °C; _w = 8°; data data corrected for dynamic q effects. For dry (baseline) data: corrected for dynamic q effects. For dry (baseline) data: c I = 2.087; _ = 0.019; coefficient of variability, 0.9 percent. Cl, max = 2.646; _ = 0.031 ; coefficient of variability, 1.2 percent.

r IRT reference / static pressure top Splitter wall ---x r \\ Front edge of ground plane .::::::: r IRT reference iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiii!i!i!!iiii!i_iiiii_i_i_41i;iii_i_iii_i_i_i_iiiiiii;i_iiiiiiiiiiiiiiiii_i_i;iiiiiiiiiiiiiiiiiii_iiiiiiiiiii :i8i_i8i:i_i:i:i!i_!i_ii:_i_:_i_:_::_8_:!8!8_!:_8X_!_!_$_:i_8!_i:!8!8!8!8i:i8i_!8i_:i::_ static pressure top :::::::t i_i{i

t

Front view Tunnel Jnnel Aft edge of wall --x wall -_, ground plane Plan view Figure 133.--Reference static for three-dimensional half model. Tunnel was calibrated with and without ground plane Height above Flow floor, in.

.10 .08 4.115m (13 5 ft) Referenco static/_ili I" peak // pressure port :z/I_i1 .O6

I±

H

._:.%_ _:::_.............._:::: :_.i 0.457 m (1.5 ft) .O4

I-l-

.02 ¢- _/t "-- Chosen PS, ref location .2 _ _/_ t',/--36 Q)

I

20 3O-""-- 40 _ 50 60 :3 Plan view 2 -.02 O..

2.743 m (9 It) _- -.04 1.524 m (_ It) -_ i i i ii i ii i ,_ _ r r -.02

T

1.829 m -.08

(6 n)

procure port--/ l_i]

_L

-.10 Rear view Cp, model = Cp, modelin- Cp, modelout Figure 134.--Lines ofchange inmodel pressure coefficient showing reference sta_ location chosen. TWo-dlmensionalmodel. Potential flow panel method (A502) results.

Run time, dctldl, sec sec --I B-run 17-23 -O.017 23 - 27 -0.008 27 - 31 -0.052 3 ........

G" 341 ._'_" _'_ 2.0 c¢/dt - - ,, "¢3

_E I _'_ .... -" 1.51--

dctlo_ = -0.052

o

1.0 ,..I

I 1 I I

I I I I I I I I I I 5 I

-I 0 4 8 12 16 20 24 28 32 36 40 0 10 20 30 40 50 Run time, sec Time, sec Figure 135.--Dependenco of lift coefficient on run time for two- Figure 136,_Basis for dynamic q correction. Two-dimensional, flaps dimensional model in flaps 5, sealed-slat configuration: dynamic 5, sealed-slat configuration; dry wing; o= w = 8.1°; run 524.

q effect. Dry wing, temperature, 20 °C.

Next: Appendix F →

Appendix F

Tabulations of Fluid Aerodynamic Effects

This appendix contains tabulations of the fluid aerodynamic pitching moment, and fluid effect on rolling moment are effects (tables XVII to XXIV). For the three-dimensional half tabulated. For the two-dimensional model, lift loss, drag model, the lift loss, drag increase at takeoff safety speed, increase at takeoff safety speed, and takeoff acceleration drag average takeoff acceleration drag increase, fluid effect on increase are tabulated.

1"ABLE XVII.--THREE-DIMENSIONAL IIALF MODEL LIFT LOSS DATA IAll lift h,ss vtdues in percent.I (a) Flaps 5. sealed sial configuratiolt. _ound plane in T = -20 *C Fluid T - 0 *C T = -10 "C AC I (7*) AC t ..... AC t (7*) ACI ....

AC_ t 7") AG.=,_ I ...... 1.7 2.8 3.9 6.8 2 ...... 8.6 9.9 3 2.8 4.6 5.3 7.0 4.7 8.6 4 ...... 3.2 3.2 3.1 4.0 (b) Free air dala: fluid 3; T - -20 +C Cqnlfigt|ration At ACI (7 °) At AC 1....

Flaps 5, sealed slat 7.6 7.2 Flaps 5, gapped slat 10.3 155 Fhlps 5, sealed slat, 20* aileron 5.5 5.3 Flaps 15, gapped slat 90 I 1.3 (c) Flaps 15, gapped slat configtlratioll, gl-Otltld plane in Fhfid T'0*C T - -i0 *C T - -20 *C AC,. (7") ACt .... &G (7*; AC t .... ACt (7") ACL.,. _ .

4.0 4,9 9.1 10.8 I 1.9 12.8 8.0 8,8 10.9 12.8 5.7 6.9 TABLE XIX.--AVERAGE TAKEOFF ACCELERATION TABLE XVIII.---THREE-DIMENSIONA1. MODEL DRAG INCREASE FOR TttREE-DIMENSIONAL DRAG INCREASE AT TAKEOFF SAFETY SPEED HALF MODEL IAt CL currespculdin_ to u_xl_,,,, = 7_.1 [a - 0°; time - 15 s_'; ,mtmud plaite in.[ Fluid T-O*C T- -10°C T--20°C Fluid T- 0"C T--100C T--20°f' Drag increase, AC_,, pcrcem Drag in,,:rease, ACt,. ,ercent Flaps 5, seMed slats clmfigu, allon Flat)s 5, sealed sial c_)llfigur_tlio]l .... 0.9 7.0 .... 5.4 7.9 .... 18.2 ......

.... 18.3 ....

I 0.0 14.2 I 1.3 23.6 22.5 17.7 .... 40 8.1 .... 7.8 22.6 Flaps 15. gapped slats ctmfigur,'_llioll Flaps 15. gapped sial configtu-ation 0.9 20.7 .... 0.8 q.4 18.2 .... 14.0 ....

14.2 24,05 .... 8,0 15.4 8.75 ........ 6.4 "rABI E XXI --N 1.11D EFFFCT ON ROI.I.ING TABI.E XX.- FI.LIID EFFECT ON PITCHING MOMENT qtlREE-DIMENSIONAI. ItAI F MODEL MOMENr OF FHREE---DIMENSIONAL ItALF MODEL ITeml_r'talure. -20 °C; _'l_tttltl plane inl [Tcnllerature. -20 °C; _lOlilld iqalle in; lluid Oll left wing t,ld.X'.l Fhlid Ar 7 ° At CL,m_ x Pitching mt,ntent. Cat, 0.25C Fluid AI 7 ° At CL,ma x Flaps 5, sealed slat c_nfigutation Rollillg illotnetlt il_remt'ilt, 1 -0.034 0063 At:l, percent Flaps 5. seal slals configulatitm 3 -.027 .053 -4.0 -7.6 4 - .034 .0_, 1 Dry - .047 .087 -36 - 9,q Flaps 15, gapl)¢d sial ¢onfigttrali.n -1.1 -4.7 I - O, 134 -0.075 Fhlps 15. g'll,ped shits omfigur:ititm 3 ...............

1 -7.o -128 3 -.122 -.075 2 ......

4 -.143 -.084 3 -10.8 - 150 Dry -.178 -.080 4 -5.6 -8.1 TABLE XXII.--TWO-DIMENSIONAL MODEL LIFT LOSS DATA

Fluid T - 0 C T - -.10 °C T - -20 C

_,at8° I _, .... _,a,g* I _,°_ ACt at 8° ] At'/.mL, " Lilt loss. perceHt Fhlps5, sealedsl_ltconfigur;itil_n --- 48 27 7.0 5.1

I

2 --- 11.4 6.0 13.2 14.4

3 4.8 5.9 7.1 5.1 9.4 7.0

4 --- 2.5 1.3 5.3 3.0

2.1 --- 4.2 1.2 6.3 4.8

2.2 --- 6.2 1.8 7.1 4.9

3.1 5.t 0 4.4 3.5 5.9 2.9

3.2 --- 5.3 5.2 5.7 4.4

4.1 3.4 0 5.0 2.8 7.5 33

4.2 --- 4.0 14 5.2 4.5

5.1 1.0 0 2.4 1.4 5.5 3.8

5.2 --- 4.4 4.7 5.5 3.8

Flaps 5, gapped slat ci_nt]gumtion --- 4.0 6.2 8.8 10.7 --- 13.3 14.9 18.6 27.6 --- 88 I 1.4 I 1.0 14.6 --- --- 3.3 4.6 5.4 46 TABI.E XXIII.--TWO-DIMENSIONAI. MODEL DRAG TABLE XXIV.--AVERAGE TAKEOFF ACCELERATION INCREASE AT TAKEOFF SAFETY SPEED DRAG INCREASE FOR TWO-DIMENSIONAL MODEL lAt Ct conesponding to 0_.,_,o - 6.5* excep! a_ noted.I Fluid T - 0 *C T - -10 *C T - -20 °C Average take,If accelertdic_l_ tlra$ it_rease, Fhtid T'O*C T--10°C T'-20"C AC, I. percent M,_del drag iucrezse, A_l Flaps 5. se'ded slat c_alfi_tlralioll Flaps 5, sealed slat c,onfiguration I 25.9 | .... 23.6 39.0 2 62.2 2 ....

66.4 03.9 3 32.5 3 26.0 50.0 56.3 4 39.2 4 .... 23.2 18.8 2.1 .... 34.0 35.4 2.1 .... 23.3 26.2 2.2 .... 34.7 40.2 2.2 .... 34.2 3.1 47.9 36.8 38.5 47.5 3. I 20.3 20.5 34.8 3.2 .... 40.7 38.8 3.2 ....

20.5 37.4 4.1 38.5 22.8 25.3 4.1 23.4 12.4 30.0 4.2 .... 281 23.0 4.2 ....

5.2 16.4 5.1 23.9 266 24.5 5. I 12.9 11.7 24.4 5.2 .... 25.7 30.1 5.2 ....

20.0 28.2 Flaps 15, gapped slat c_mfi_urntion Fhq_s 15. gapped slat c_mfiguralil,n 10.3 26.8 65.2 83.1 32.9 51.1 8.8 19.4 Form Approved

REPORT DOCUMENTATION PAGE OMB No OZO,,-O1a8

PtJd_4_ ml_ bocclerl for th_ ¢:o_a(:t_ of in.re.ion is estm_leO to averse 1 hour per rm_oonse, induOing the llme lof rm/mwinQ inl_;'quc_om. INBa_hmg exmzng Oata sour(el;, 81¢KI Itla_IIJNI_ _ _ IIqlOe¢l. _ ¢:Oml314_ _ 4lrt0 r_ng the Cofl_[On Of IfitolmstJOn. Ser_l ¢ofllnlort_ i_Rrl;lin_ Ithls 13or01_ lstJn_lle 04" _ ocher _10_1¢1 of this (:oaecllon Of inlomultio_, including lug_ 1or reduOng this btJrOen, to Washc, gton HeadClUatters Semaces. Direclorltte for knfo_natioft Opefalm im¢l Reports. 1215 Joffecson Davm Highway. Suite 1204. Arlington. VA 222024302. and to the Office of Manageme_ an0 Budget. P_ Reduction Prole¢t (0704-0188). Wlu_Nnglon. DC 20503.

1. AGENCY USE ONLY (Leave t)/ank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED Au_;ust: 1992 Technical Paper 4. "ITrLE AND SUBTITLE 5. FUNDING NUMBERS Lewis Icing Research Tunnel Test of the Aerodynamic Effects of Aircraft Ground Deicing/Anti-Icing Fluids s. AUTHOR(S) WU-505-68-1 l L. James Runyan, Thomas A. Zienen, Eugene G. Hill, and Harold E. Addy, Jr.

8. PERFORMING ORGANiZATiON 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) REPORT NUMBER National Aeronautics and Space Administration Lewis Research Center E-5808 Cleveland, Ohio 44135-3191 I10. SPONSORING/MON_ORING 9. SPONSORING/MONITORING AGENCY NAMEStS) AND ADDRESStES) AGENCY REPORTNUMBER National Aeronautics and Space Administration NASA TP-3238 Washington, D.C. 20546-0001 11. SUPPLEMENTARY NOTES L. James Runyan, Thomas A. Zierten, and Eugene G. Hill, Boeing Commercial Airplanes, Seattle, Washington; Harold E. Addy, Jr., NASA Lewis Research Center.

12b. DISTRIBUTION CODE 12a. DISTRIBUTION/AVAILABILITY STATEMENT Unclassified - Unlimited Subject Category 03 13. ABSTRACT (Maximum 200 words) A wind tunnel investigation of the effect of aircraft ground deicing/anti-icing fluids on the aerodynamic characteristics of a Boeing 737-200ADV airplane has been conducted. The test was carried out in the NASA Lewis Icing Research Tunnel. Fluids tested include a Newtonian deicing fluid, three non-Newtonian anti-icing fluids commercially available during or before 1988, and eight new experimental non-Newtonian fluids developed by four fluid manufacturers. The results show that fluids remain on the wing after liftoff and cause a measurable lift loss and drag increase. These effects are dependent on the high-lift configuration and on the temperature. For a configuration with a high-lift leading-edge device, the fluid effect is largest at the maximum lift condition. The fluid aerodynamic effects are related to the magnitude of the fluid surface roughness, particularly in the first 30 percent chord. The experimental fluids show a significant reduction in aerodynamic effects.

15. NUMBER OF PAGES 14. SUBJECT TERMS Rheology; Non-Newtonian fluids; Deicing 16. PRICE CODE A07 - 19. SECURITY CLASSIFICATION 20. LIMITATION OF ABSTRACT 17. SECURITY CLASSIFICATION 18. SECURITY CLASSIFICATION OF THIS PAGE OF ABSTRACT OF REPORT Unclassified Unclassified Unclassified Standard Form 298 (Roy, 2-89) NSN 7540-01-280-5500 Prescr|DeO by ANSI SIIJ Z39-18 NASA-La gley, 1!_02

Overview

Appendix A View in PDF

Appendix A

Fluid Holdover Time, Rheological Properties, and Water Content

20 *C, 0 °C, - 10 °C, and -25 °C. A Brookfield viscometer

This appendix contains rheological properties and water

and SCR4-34/13R (all fluids except fluid 1 and fluid 4.2 at

Technology. The fluid holdover times were determined by

control was maintained using Brookfield EX-200 and Neslab

Fluid Holdover Time

coolers. Data were recorded using the Brookfield DV Gather

The fluid holdover times in freezing rain are shown in table I

Tables IV to XV contain the rheological data for all of the

(p. 4). The data sources are also noted in that table. Holdover

fluids. Some of these data at - 10 °C are shown in the plots

times are shown for the four basic fluids (fluids 1, 2, 3, and

of viscosity versus shear stress of figure 58. The four basic

4). Holdover times are also shown for the four experimental

fluids (fluids 1, 2, 3, and 4) are shown in figure 58(a). The

3.2, 4.1, and 5.1). The AEA freezing rain endurance test

Fluid Water Content

Fluid Rheological Properties

The water contents of all 12 fluids tested are shown in table

XVI. These results were determined by Boeing Materials

The fluid rheological properties were determined by Boeing

tunnel test. Viscosities were determined for each fluid at

TABLE VI.--FLUID 3 RHEOLOGICAL PROPERTIES TABLE VII.--FLUID 4 RHEOLOGICAL PROPERTIES

TABLE VIII.--FLUID 2.1 RHEOLOGICAL PROPERTIES

I (a)l

I

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(c) I

Appendix B View in PDF

Appendix B

Three-Dimensional Half Model Force Data

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Appendix A

Appendix B

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Appendix C