Results of an experimental program investigating the effects of simulated ice on the performance of the NACA 63A415 airfoil with flap

NASA-CR-168288 19840008077

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[ RESUL T S O F A N EXPERIMEN T AL P R O GRAM INV E S T IGA T ING TH E E F F EC T S OF SIMU L A T ED .I ICE ON THE PERFORMANCEOF THE NACA 63A415 AIRFOILWITH FLAP R . 3 . Z a gu l l ,M. B. Brag g , a nd G. M. Gr ego r ek The Oh l o State Un l verslt y Columbu s , Ohl o 3 a nua r y 1 98 4 !, ' z ! , : .,;4 I r e , ' _ t Fv R_rr_ t _ ....

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Lewis Resear c h Center Under Grant NAG3-28 TABLE OF CONTENTS PAGE NOMENCLATURE iii INTRODUCTION I EXPERIMENTAL METHOD 2 Equipment 2 Data Reduction 3 RESULTS AND DISCUSSION 5 Aerodynamic Measurements 5 Flow Visualization 6 Presentation of Data 8 SUMMARY AND CONCLUSIONS 9 REFERENCES i0 FIGURES Ii APPENDIX 23 Run Summary 23 Cumulative Plots 26 C_ vs e 26 C_ vs C d 42 Cm vs C_ 45 Cp Distributions 61 i NOMENCLATURE c Airfoil chord length, m C d Drag coefficient, D / q_c C_ Lift coefficient, L / q_c C Moment coefficient about the quarter chord, . m M / qc 2 Cp Pressure coefficient, (P - P=) / q_ K / c Roughness height P Local static pressure, N / m 2 P Free stream static pressure, N / m 2 q_ Free stream dynamic pressure, N / m 2 T Temperature, OF V Velocity in knots x / c Horizontal coordinate z / c Vertical coordinate e, AOA Angle of attack, degrees _f Flap deflection, degrees iii INTRODUCTION The test program described in this report is an extension of a study begun in 1981 to provide needed information on the perfor- mance degradation of airfoil sections resulting from rime and glaze ice accretions. Its primary objectives were * i) To expand the current database of performance data on the 63A415 with simulated ice to include flap deflection.

2) To further study the flowfield in the area of the ice accretion through pressure distributions and flow visualization techniques, which can then be used to evaluate the accuracy of the theoretical analysis methods currently being developed.

3) To obtain data on a simulated glaze ice shape that scales down to a 6 inch chord model and will be tested in the OSU Tran- sonic Airfoil Wind Tunnel Facility. These data will be used to compare the aerodynamic qualities of the NASA Icing Research Tunnel and the OSU tunnel, and to evaluate a lift measuring system based on wall pressures.

Mr. Richard Freuler, Senior Computer Specialist at the Aeronautical and Astronautical Research Laboratory, developed the software needed for the data acquisition system. Mr. Steven Thompson, an under-graduate research assistant, modified the software and performed the data reduction for this test.

I EXPERIMENTAL METHOD Equipment Testing was performed in the NASA Lewis 6' x 9' Icing Research Tunnel (IRT). The airfoil model used was the NACA 632-A415 with a 1.36 m chord and a moveable flap with deflections of I0°, 20° , and 30° . The airfoil and flap were pressure tapped using 1 / 8" OD strip-a-tube attached to the airfoil surface. In addition, the model was fitted with five simulated ice shapes (Figures IA-IE): I) Generic Glaze 2) Glaze 3° 3) Rime 3° 4) Glaze 7° 5) Rime 7° Aerodynamic data were taken on the first three shapes and flow visualization was performed on all five. The Generic Glaze shape was derived from the work of Ingelman-Sundberg I. This shape was chosen because it scales to a convenient size on the 6" chord model which will be tested in the OSU Transonic Airfoil Wind Tunnel Facility.

The Glaze 3, Rime 3, Glaze 7, and Rime 7 shapes were chosen from a series of ice growths generated during an actual ice accre- tion study in the NASA Lewis Icing Research Tunnel 2. They repre- sent typical climb, high angle of attack and low velocity, and cruise, low angle of attack and high velocity conditions.

In order to add the surface roughness characteristic of natural ice shapes, aluminum oxide grit with a K / C = .00058 was attached to the glaze shapes with a spray acrylic adhesive. A grit with a _o°_ K / C = .0012 was added to the rime shapes.

On-line data acquisition and reduction were accomplished using the OSU Digital Data Acquisition and Reduction System 3 (DDARS - J / figure 2). The central processing unit is the DEC LSI-II micro- computer. Input and output is through a teletype terminal and mass data storage through a twin floppy disc drive system. Analog data signals from the transducers and wake probe slidewire systems are fed into an analog front end which conditions the signal and con- " verts it into a digital format.

Airfoil pressures were obtained through a Scanivalve trans- ducer arrangement, while drag data were measured using a wake probe with total and static ports. The voltages from these systems as well as those from tunnel total and tunnel static transducers were input to the analog box and then to the computer for on-line reduc- tion (figure 3).

In order to visualize the flow in the leading edge region, a splitter plate 4 was constructed which could be positioned between the upper and lower segments of the attached ice shape. (See figure 4). Small drops of oil-based paint were then applied to the plate in the regions of interest and the tunnel then brought up to speed. Videota p e was made of the movement of the drops and still photo_raDhs were taken after no further movement was observed.

Data Reduction The DDARS system provides the test engineer quick-look pres- sure distributions as well as integrated values of C_, Cm, and Cd.

This permits maximum use of tunnel time.

An interactive computer program was written for the final data reduction on the OSU Harris / 6 computer system. The raw data files from the IRT test were transferred to the Harris from the LSI-II microcomputer. The program converts Scanivalve voltage from each model tap into a pressure coefficient The user is given a plot of the final Cp distribution for each element (main and flap) on a Tektronix CRT and can control any re-reduction required using the terminal cursors. The program then integrates the distribution to " get lift and moment coefficients.

The drag coefficient is calculated using the Jones Equation 5.

The wake is displayed on the graphics terminal and the user enters the integration limits using cursors. If the operator sees that the probe traverse was not large enough to capture the full wake, that run reduction can be bypassed.

RESULTS AND DISCUSSION Aerodynamic Measurements Data were taken on the following simulated ice accretions as well as the clean airfoil; i) Rime 3 Rough 2) Glaze 3 Rough 3) Generic Glaze Smooth • 4) Generic Glaze Rough In addition, for each configuration flap deflection was varied from 0-30 degrees.

The glaze ice Cp distributions show the characteristic adverse pressure gradient where the flow is forced to negotiate the large change in surface slope at the tip of the horns. These pressure spikes promote separation and tend to decrease C_max and increase the drag coefficient. The separated zone is clearly seen as a region of constant pressure in the Cp distribution in the area behind the glaze ice horn.

From the pressure distributions, it is observed that the flap was stalled for most of the runs. This separation is again char- acterized by a region of constant Cp. A previous investigation by W. R. Krolak 6 on the Beechcraft Sundowner, equipped with a NACA 63A415 airfoil, shows this same trend in flight test data.

From Table I and figure 5, it is clear that the penalties associated with ice show up in reductions in C_max and estall" The G3 shape showed a reduction in C_max over the clean case of 0.2 - 0.4, and a reduction in estall of as much as 4 ° for the 6f = 30° case. Similar reductions were seen for the generic and rime shapes.

Due to the position of the wake probe, drag data could only be taken on 6f = 0° cases. Cumulative plots of C_ vs. Cd show TABLE I PERFORMANCE DEGRADATION WITH SIMULATED ICE CLEAN G 3 GEN R3 ,If I0 20 30 i0 20 30 i0 20 30 I0 20 30 C vm a x 1. 8 2.0 2 . 2 1 . 4 1.7 2.0 1. 2 1.5 1 . 7 1 . 5 1 .7 5 1 . 95 _ s tall 14.0 12.5 11.5 10.5 9 . 5 7.5 7 .5 5.5 10.5 8.5 6.5 "LO -6.5 -i0.0 -13.0 -6.0 -12.5 -6.0 -i0.0 -6.0 - -ii.0 the increase in drag caused by the ice shapes. For example, at C_ = .4, a 20% increase in drag over the clean airfoil was observed when the R3 rough shape was attached, and a 30% increase for the G3 rough shape. Interestingly, the presence of roughness on the Generic Glaze shape was not found to be very crucial. This is due to the large laminar separation bubble in the region of the ice shape, which tends to be the prominent source of pressure drag.

From the cumulative plots of Cm vs C£, it is observed that at the lower lift coefficients the effect of the ice shape is almost negligible. However, at the higher C%'s, for example at low speed with the flap deflected , more positive Cm's were observed with the simulated ice than for the clean airfoil.

Flow Visualization Using the splitter plate arrangement, discussed previously, the flow about the simulated shapes was recorded. Of particular interest were the separated zones observed with the glaze shapes.

These laminar separation zones were photographed and later the coordinates of the separated streamline were digitized from these records. Figures 6 and 7 are representative of the observed flow patterns. Figure 6 clearly shows the Generic Glaze shape at = 1.7 ° with its separated zone behind the horn. Figure 6 is of the same configuration but at e = 5.6 ° , and clearly shows the characteristic recirculation region. Figure 8 shows the G3 shape at e = 5.6 °.

• The authors discovered during the analysis of the photos that the splitter plate extended too far into the flow ahead of the stagnation region between the glaze ice horns. The splitter plate boundary layer then separated due to the adverse gradient from the airfoil flowfield. This 3-D flowfield created vortices which were shed downstream and affected the flow patterns recorded.

This is particularly evident in figure 7 where the streamlines converge due to the influence of these shed vortices. However, qualitatively the data provides some interesting clues to the shape and extent of the laminar separation bubble.

Further investigation was performed at Ohio State using two different splitter plate configurations. A scaled-down version of the splitter plate utilized in the Lewis IRT and a smaller one with the leading edge reduced were tested on a GAW-I airfoil with a simulated ice shape. Flow visualization techniques confirmed the authors' hypotheses that vortices were shed downstream due to the severe pressure gradient induced by the ice shape on the splitter plate. It was observed that the reattachment point was shortened by as much as 3% under these test conditions as a result of the larger splitter plate. This value cannot however, be directly applied to the 63A415 airfoil_in the Lewis test.

Rather, the reader should realize that qualitatively this shows that the observed reattachment point was moved forward due to the presence of the splitter plate. In addition, it must be pointed out that this method of visualization does not actually display the position of the separated streamline. Rather a position above the zero velocity line in the separated zone between the recirculating flow is measured.

Presentation of Data A tabulated run summary is included in the appendix of this report. It is organized by configuration: I) clean, 2) rime 3 rough, 3) glaze 3 rough, 4) generic glaze rough and 5) generic glaze smooth. Following these tables are the cumulative plots of C_ vs e, Cm vs C%, and C_ vs Cd. Lastly, the pressure distri- butions are included and ordered in the same sequence as the run summary tables.

Data reported with zero flap deflection was taken at approximately Re = 4.2 x 106 and M = 0.13. Due to the large loads on the model, data at all flap deflection angles greater than zero, were taken at approximately Re = 3.3 x 106 and M = 0.i0.

No tunnel wall corrections have been made in the data.

o_ SUMMARY AND CONCLUSIONS A typical general aviation airfoil, the NACA 632-A415 , was outfitted with simulated ice accretions and tested in the NASA r Icing Research Tunnel. Pressure distributions were obtained for a variety of flap deflections and angles of attack. As a result of this study, the following observations can be made; i) The airfoils with simulated ice shapes showed large increases in drag and heavy penalties in C_.. and estall A shift in _LO was also observed. These reauctlons in performance would be of particular importance to the pilot in a landing con- figuration with the flap deployed and power reduced.

2) Measured pressure distributions and flow visualization show the separated zone behind the horn of the glaze shapes and the severe adverse pressure gradients which lead to the separa- tion.

3) Surface roughness for the Generic Glaze shape was not a crucial factor in the drag observed. Rather, the prominent effect was the large separated zone.

Q Further investigation is necessary to document the flow character- istics reported. More detailed Dressure distributions should be obtained, particularly in the region behind and between the glaze ice horns. Also, while flow visualization provides valuable insight into the flow in the separated zones, quantitative data must be gathered here before an analytical model can be develoDed.

REFERENCES i. Ingelman-Sundberg, M., Trunov, O. K. and Ivaniko, A., "Methods for Prediction of the Influence of Ice on Aircraft Flying Char- acteristics," Swedish-Soviet Working Group on Flight Safety, 6th Meeting, 1977.

2. Bragg, M. B., Zaguli, R. J. and Gregorek, G. M., "Wind Tunnel Evaluation of Airfoil Performance Using Simulated Ice Shapes," NASA Contractor Report 167960, November 1982.

3. Freuler, R. J. and Hoffmann, M. J., "Experiences with an Air- borne Digital Computer System for General Aviation Flight Test- ing," AIAA Paper No. 79-1834, presented at the AIAA Aircraft Systems and Technology Meeting, New York, New York, August 20-22, 1979.

4. Pfeiffer, N. J. and Zumwalt, G. W., "A Computational Model for Low Speed Flows Past Airfoils with Spoilers," AIAA Paper No.

81-0253, Presented at the 19th Aerospace Sciences Meeting, St.

Louis, Missouri, January 12-15, 1981.

5. Schlichting, H., Boundary-Layer Theory, Sixth Edition, McGraw- Hill, New York, 1968.

6. Krolak, W. R., "In-Flight Investigation of the Aerodynamic Characteristics of a Wing Equipped with an Upper Surface Lead- ing Edge Modification," Master's Thesis, Ohio State University, 1981.

7. Kunchal, David, "Splitter Plate Analysis," Final Report for AAE 693, Ohio State University Aeronautical and Astronautical Engineering Department, October 1982.

i0 I I x l c z l c 0 004455 0.01982 -0 00278 0.01815 -0 01204 0.01426 -0.01889 0.00963 -0 02454 0.00278 ' -0 02593 -0.00389 L ! -0 02296 -0.01019 i- i -0 01593 -0.01315 -0.00796 -0.01407 0.00093 -0.01463 I FIGURE IA. R3 ICE SHAPE ii x l c z l c 0.00000 0.01157 -0.00417 -.00630 -0.00815 0.00000 -0.01157 -0.00602 -0.01315 -0.01167 -0.01130 -0.01519 -0.00778 -0.01685 -0.00139 -0.01759 0.00370 -0.01815 0.01000 -0.01852 FIGURE IB. R7 ICE SHAPE x / c z / c -.002 3 2 .01435 -.01019 .01389 -.01667 .01407 -.01944 .01315 -.01907 .01019 -.00648 .00241 -.00556 -.00 5 9 3 -.00889 -.0120 4 -.00389 -.01 3 89 .00667 -.01 4 82 ' FIGUREIC. GL A ZE 3 SIMUI A _"]_D ICEACCRETION A NDPRES,N 3 RE T A Pl O CATIONS • 13 x / c z / c .0009 3 .01759 -.00278 .01620 -.00648 .00972 -.01667 .00778 -.01796 .00519 -.01157 -.00093 -.00509 -.00602 .00556 -.01759 •01435 -.02732 •02500 -.02593 FIGURE ID. GL A ZE 7 SIMI g _ A TED ICE ACCRETION AND PRESSURE TAP LOC A TIONS x / c z / c 0.01985 0.0 3 807 0.00427 0.0 3 807 - 0.011 33 0.03807 - 0.0 2 4 5 2 0.0 3 5 84 - 0.021 3 6 0.0226 4 - 0.018 5 7 0.00706 - 0.02099 - 0.0085 4 - 0.02452 - 0.02229 - 0.00613 - 0.02 4 14 0.01467 - 0.02414 FIGURE IE. GT_, _RIC GL :u ZE Sh-MUIA21_ ICE ACCRETION / %NDPRESSURE TAP lOCATIONS ANALO G FKONT FLOPPY DISC S Y S TEM p O WER SUPPLY FIGURE 2. OSU DIGITAL DATA ACQUISITION AND REDUCTION SYSTEM

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'+i ,I I ]m • i DISC PDP- Ii ANALOG WAKE StJRVEY • i DRIVE MICRO- "-- PROBE DRIVE

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STATIC _RANSD:J_ERS I ,+ TUNe,EL STATIC _ AIRSPEED AND I TRAN_DUCEHS WING PRESSURE TAPS _ CANIVALVE TO I "t i _i i - i:i ...+ ! FIGURE 3. OSU DATA ACQUISITIONSYSTEM i AS USED IN THE NASA LEWIS IRT i .I !t ;I i , 17 :P , .!

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FIGURE 4. 63A415 WING WITH SPLITTER PL _TE IN LEWIS ICING RESEARCH TUNNEL i 'i .i .i ,' t . r i .`1 I i_ 3 - !

F b I "'ii .I :i i O ,F 2- O ,'i L O -_ _ A !

• _ n .1 max < A i O Clean i 1 i i [] Rime 3* .i • <> Glaze 3* /k Generic Glaze i .'in 0 I I I 0 I0 20 30 i. _f (degrees) .ii FIGURE 5. CHANGE IN C_ , WITH SIt.RI L ATED ICE SItAPES i max •i "(_ ,: 0° .! = Cases from 1982 IRT Test 2) iI _- -!

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ex = 1. 6° tv M = 0.152 o Re = 4. 7 x 10 FIGURE 6. SPLITTER PLATE PHOTOGRAPH OF UPPER SURFACE OF THE GENERIC GLAZE R0UGH ICE SHAPE ex = 5.6 M = 0.152 Re = 4.7 x 10 FIGURE 7. SPLITTER PLATE PHOTOGRAPH OF UPPER SURFACE OF THE GENERIC CLAZE ROUGH ICE SHAPE 0.=5.6° M=0.153 N N Re=4.6 x 10 FIGURE 8. SPLITTER PLATE PHOTOGRAPH OF UPPER SURFACE OF THE G3 ROUGH ICE SHAPE .~' .. '. ~ APPENDIX Run Summary RU N # A O A FLA P V (K T ) TO( F ) P RE SS . CL C D CH DEF A L T . ( F T) CLE A N 48 1 0 .6 0 . 0 103 . 43 7 7. 0 8 3 8. 0 1 . 33 9 3 0.025 6 - 0 , 0 9 5 49 11.6 0.0 101.9 2 7 5.0 83 2 .3 1. 44 10 -0.108 60 - 5 ,4 0.0 10 2 . 2 3 50.0 85 2 .9 -0. 2 3 2 6 0.0110 -0.044 6 1 - 2 . 4 0 . 0 101. 39 5 2 . 0 8 4 4. 3 0 . 0 710 0 . 0 1 05 -0. 0 46 62 -0. 4 0.0 100.1 8 69 .0 839 . 2 0. 3 1 26 0.01 08 - 0.0 49 63 1 . 6 0 .0 10 2 .8 4 7 5 . 0 8 6 9 . 4 0 . 5 43 1 0 .0112 - 0.05 9 64 3 .6 0.0 101.05 6 7.0 8 57. 2 0 . 722 0 0.01 28 -0.05 9 65 5. 6 0.0 1 0 2 , 25 70.0 8 7 0 . 5 0 . 9 0 2 0 0.01 44 - 0.05 9 66 7. 6 0.0 101. 64 7 2 .0 8 69 . 9 1.100 2 0. 0 1 69 - 0.0 7 5 67 8 .6 0 , 0 101 , 0 3 74 ,0 87 1.1 1 .1 69 1 0 . 01 96 -0. 07 7 6 8 9 . 6 0 , 0 10 3 .57 7 5 . 0 8 9 2.1 1 .22 79 0.0 220 -0.075 69 10. 6 0 , 0 101.74 71 .0 878 .5 1.31 9 8 0 . 0 2 75 - 0.0 92 70 11.6 0.0 101. 2 5 73 . 0 880. 2 1. 422 5 0 .0 3 00 - 0.0 9 0 81 - 2 . 4 0.0 10 2 . 5 9 62 .0 1083.5 0.08 8 1 0.0118 -0.04 9 8 2 - 0. 4 0.0 101. 7 9 57. 0 1 0 7 9. 6 0. 3 01 7 0.01 24 -0.051 8 3 1.6 0.0 10 2 . 24 6 8.0 1087 . 2 0 .505 9 0 , 01 2 5 - 0. 0 5 6 8 4 - 6.4 i0.0 7 8.01 73. 0 9 0 7. 7 - 0.00 97 -0. 1 1 7 85 -2 , 4 1 0 .0 7 8 .3 1 70 . 0 9 0 2 , 1 0. 43 5 2 -0 , 1 29 8 6 - 0. 4 10 .0 7 8 .7 4 7 0, 0 903 . 7 0. 669 4 - 0, 1 32 8 7 1. 6 10.0 8 0 . 3 0 69 . 0 9 1 5. 4 0 , 90 7 5 -0 .1 42 88 3 . 6 10.0 7 8.15 69 .0 9 0 6 .1 1.1058 -0,1 42 8 9 5.6 I0.0 7 8 . 51 67 .0 9 0 6 .8 1. 22 0 2 -0 .133 9 0 7. 6 10.0 7 9 .2 9 6 8.0 9 1 4 .0 1.3540 -0.1 36 9 1 9 . 6 10.0 7 7. 6 8 6 7 .0 9 02 . 1 1.5 2 55 -0.15 3 92 11. 6 I0 . 0 80 , 5 3 6 7 .0 92 4 . 2 1 .7 29 6 - 0 .17 8 93 1 2 , 6 i0 . 0 7 9 .2 6 65 . 0 9 1 7 .8 1. 7 155 -0 . 1 7 8 94 1 3 . 6 I0.0 7 8 . 44 6 6.0 9 10.8 1.8 233 - 0.1 96 9 5 -6 , 4 2 0. 0 81 , 2 0 64 .0 93 0 , 0 0. 42 58 - 0 . 2 1 9 96 -2 , 4 2 0. 0 7 9 .7 5 6 5 .0 922 . 5 0 .8 9 38 - 0. 23 1 9 8 9 . 6 2 0.0 78. 67 68 . 0 914 . 1 1.8 7 1 4 -0. 2 55 99 3 . 6 2 0.0 7 7 . 82 6 6 .0 9 09. 8 1. 463 5 - 0. 2 31 1 0 0 - 1 0 , 4 30 . 0 7 8 , 35 64 .0 9 1 7 , 7 0 . 3 0 8 4 -0 , 2 88 1 0 1 - 6 . 4 3 0. 0 7 8 . 5 7 6 6 , 0 9 1 3 , 7 0 .7 973 - 0, 3 0 4 1 0 2 -2 , 4 3 0,0 7 9 . 80 66 . 0 92 1 , 2 1 .22 8 7 - 0 , 3 03 10 3 1 , 6 3 0 .0 7 8 , 0 9 6 5 ,0 90 7. 6 1 . 74 1 3 - 0 . 3 1 7 1 0 4 5.6 30.0 7 8 . 8 6 64 .0 9 1 0.5 1. 9 171 -0. 311 105 9 , 6 3 0.0 7 8. 96 66.0 9 1 3 . 2 2 . 107 1 - 0 . 328 10 6 1 0 . 6 30 . 0 77 . 39 6 5 .0 905 , 2 2 . 2 7 60 - 0, 34 9 1 07 11 , 6 30 .0 7 9 . 7 5 6 5 . 0 92 1 , 8 2 , 1 74 1 -0 . 346 1 3 5 1 3 . 6 1 0, 0 7 8 . 26 7 9 ,0 7 0 8.8 1 ,7 9 0 6 - 0 .1 2 5 1 36 14 . 6 10.0 7 9 , 2 0 79 .0 7 1 7 ,7 1.8 02 4 - 0 ,1 34 1 37 11 . 6 2 0, 0 7 9. 0 0 67 , 0 7 1 6 . 8 1 . 955 3 -0 . 2 0 9 1 3 8 1 2 , 6 2 0. 0 80 , 18 67 .0 726 . 3 1. 9 7 23 - 0 , 208 1 39 1 3 .6 2 0, 0 79 . 7 7 73 .0 7 2 8 , 2 1 . 92 7 5 - 0 . 2 1 3 RUN # A O A FLAP V ( KT ) T° ( F ) PRESS , CL CD C H DE F A LT . ( FT ) R IH E 3 ROU G H 76 -2.4 0 . 0 101 . 48 7 3 .0 929 . 7 0.0544 0 . 016 3 -0 . 05 3 77 -0.4 0.0 102.4 9 74.0 9 3 7.0 0. 3 458 0.0140 -0.05 8 78 1 .6 0 . 0 101. 6 7 73 , 0 931.1 0 . 5213 0.014 6 - 0.048 79 3.6 0 . 0 1 01 .0 6 73.0 926. 3 0 ,74 6 8 0 . 01 70 -0.049 80 5,6 0. 0 1 02.6 7 7 4.0 941. 7 0.9326 - 0_ 046 1 5 9 - I0 .4 30 .0 78.76 7 3 .0 7 53 .7 -0. 0 371 - 0 .20 8 160 -6.4 30.0 79.60 73.0 757,8 0.7000 - 0.286 161 -2.4 3 0 .0 78.4 0 72 . 0 750. 0 1.19 3 7 - 0 .29 5 16 2 1 .6 30.0 7 9 . 9 6 72.0 7 6 2, 9 1 . 66 85 -0.2 9 4 1 6 3 5, 6 3 0.0 7 9 .28 72.0 758. 6 1 . 9 7 13 - 0 .274 1 6 4 7. 6 3 0 .0 79. 3 2 72 . 0 7 5 4. 6 1 .9 2 11 -0 , 2 3 G 1 65 7 . 6 20 , 0 79.39 72 , 0 7 63 , 2 1 . 7497 -0 , 1 9 0 1 66 9 . 6 2 0. 0 78 . 57 7 1 .0 7 59 , 4 1 .75 1 9 - 0 , 1 73 167 8 . 6 20.0 7 9 .10 72 . 0 763 .6 1 . 7041 - 0 , 17 6 1 6 8 6 . 6 20,0 77.92 72.0 7 5 7. 8 1. 6 702 -0.1 9 0 1 69 -6 , 4 10.0 7 8.30 6 6 .0 7 66 . 3 -0 , 07 3 2 -0 . 110 17 0 -2.4 1 0.0 7 9 , 19 66 . 0 772 , 2 0 , 4180 - 0 , 11 9 1 7 1 1 , 6 1 0 ,0 78 , 6 1 66 , 0 769 , 3 0 , 89 0 4 -0 , 1 1 6 1 7 2 5 .6 10 , 0 79. 15 64 , 0 774. 1 1 . 2 15 9 -0 , 1 09 1 7 3 7 , 6 1 0 , 0 79.29 64 , 0 7 73 , 9 1 , 3934 -0. 110 174 9.6 I0 . 0 79. 00 64 . 0 7 7 2 . 2 1 . 4241 - 0 . 0 88 17 5 1 0 . 6 10 . 0 7 8 , 22 62 , 0 769.3 1 . 51 64 -0. 0 90 176 1 1.6 1 0 . 0 78 . 91 63 . 0 771 . 5 1.4800 -0.093 GLAZE 3 ROUGH 71 -2.4 0.0 102 . 00 66 , 0 905.0 0.08 1 6 0 . 0 1 61 -0.050 72 -0 . 4 0 . 0 1 01 , 9 5 73 . 0 911 , 9 0 , 3 0 61 0 , 0 153 - 0 .049 73 1. 6 0. 0 101.88 73 . 0 914.9 0. 5 276 0 , 0 1 6 3 -0 . 0 3 9 74 3. 6 0 , 0 101.4 6 7 2.0 9 15,7 0 . 7521 0.0226 -0.044 7 5 5.6 0 . 0 100. 0 9 71 . 0 9 0 7.1 0 ; 8933 0 . 03 23 - 0 . 025 140 -6 . 4 1 0 . 0 78 . 01 64.0 727.3 -0. 05 4 6 -0.118 141 -2.4 10.0 79.61 75 . 0 740.3 0 . 3 8 81 -0 . 122 142 1.6 1 0 . 0 78. 8 8 79.0 734 . 8 0 . 8908 -0.1 08 143 5 .6 10 . 0 78 . 8 6 B1 . 0 738 . 6 1 , 2 35 0 - 0 . 0 9 3 1 44 7.6 1 0.0 78. 33 8 1 .0 733 , 0 1 . 34 5 9 -0 . 08 8 14 5 9. 6 10.0 7 9 .18 80.0 739 . 2 1.38 9 2 -0.088 14 6 10. 6 1 0 .0 78 . 24 7 9 .0 733 . 0 1 . 4311 - 0 . 117 147 11 . 6 1 0.0 8 0 . 3 0 76 . 0 74 6. 4 1 0 4198 -0 ,1 48 148 7, 6 2 0.0 7 9 . 96 7 6 .0 74 6 .4 1 . 7 1 96 -0.1 66 149 9 . 6 20.0 7 9 . 5 8 74 , 0 74 3 . 2 1 ,6 808 -0.202 1 5 0 8 . 6 2 0 .0 77 . 88 7 5 . 0 7 35 . 5 1.6640 - 0.173 1 5 1 10.6 20.0 7 9 .20 7 5 ,0 747.3 1. 6 80 6 -0. 2 4 3 1 5 2 6 .6 20.0 79. 5 4 74.0 747. 5 1. 66 4 7 -0.1 6 3 1 5 3 -6 . 4 3 0 . 0 7 8 . 1 0 72. 0 740 . 0 0 . 696 0 - 0 .28 8 1 5 4 -2 , 4 30 .0 7 9 .5 9 72 , 0 7 5 0 , 5 1.2116 - 0, 288 15 5 1 , 6 3 0, 0 77 . 6 7 73 , 0 743 , 3 1 , 64 8 1 -0.276 156 5 .6 3 0 .0 78 . 66 73 . 0 747. 6 1.9344 -0.2 5 0 1 5 7 7 , 6 3 0 .0 77 . 33 74.0 740 ,0 1 , 9626 -0 , 260 158 8.6 30.0 78.96 72 , 0 7 5 0.8 1.9 0 28 -0 , 277 RUN € AOA FL A P V (KT) T°( F ) PRES S . CL CD CM D E F ALT. (F T ) G ENER I C GL AZ E ROU G H 50 - 2.4 0. 0 103 , 14 7 2. 0 84 6 .8 0. 0 54 6 0. 0 338 - 0 .0 60 5 1 - 0,4 0 , 0 102.2 1 69 .0 842.4 0.2 9 4 8 0.0 3 66 - 0 . 0 41 5 2 1.6 0.0 1 02 . 60 72 , 0 84 8 ,6 0 . 5 537 0 . 044 3 - 0 . 035 5 3 3 , 6 0 , 0 101 . 58 74 . 0 8 4 3 . 6 0 , 7346 0 , 0 67 7 - 0 , 0 2 1 G E NER I C G LA Z E S M OOTH 55 -2 . 4 0 , 0 1 02 . 2 8 70 ,0 8 49 , 2 0 . 1 027 0 , 035 3 -0 , 05 9 56 -0 . 4 0 , 0 1 01 , 9 8 72 , 0 8 46 , 8 0 . 3227 0 . 0359 - 0 , 0 42 57 1 , 6 0 . 0 10 1 .96 71 , 0 8 4 5 , 4 0. 531 9 0 , 04 33 -0.0 3 0 5 8 3 , 6 0 , 0 103 ,0 9 6 9 , 0 85 5 , 1 0 ,7 26 7 0 , 06 1 6 - 0, 019 5 9 5 . 6 0 , 0 1 0 2 , 09 6 9 , 0 8 4 7 ,2 0 , 8491 -0 ,0 24 10 8 -2,4 30 , 0 79 , 1 6 65 ,0 920 , 5 1 , 2403 -0 , 27 1 1 0 9 -8,4 30.0 79 , 2 7 66 ,0 923. 3 0 , 2 0 44 ....... 0, 2 0 9 1 10 -5.4 30 . 0 79 , 3 1 67.0 927 . 6 0 . 8 4 11 - 0 .283 III 1 . 6 3 0 . 0 7 9 . 24 67 . 0 9 18. 3 1 , 6462 - 0 . 2 5 2 11 2 5 , 6 3 0 , 0 7 9 , 31 66 , 0 9 1 2 , 5 1 , 73 8 4 - 0, 299 1 1 3 7 , 6 30.0 79 . 77 66 . 0 912 , i 1 ,7 1 32 -0 , 3 43 1 1 4 -6 , 4 10 ,0 7 9 , 96 67 , 0 907 , 6 -0 , 102 1 - 0,11 3 11 5 - 2.4 10 , 0 7 8 .91 63 , 0 9 0 4 , 4 0 ,44 85 -0 , 11 1 1 24 5 .6 I0 . 0 81 . 3 9 50 . 0 7 1 2, 8 1, 1 9 37 - 0 , 0 97 1 2 5 7 . 6 10 , 0 78. 92 5 7 , 0 6 99 . 4 1. 2 1 6 1 - 0. 13 6 1 26 5. 6 10 . 0 7 9. 5 4 63. 0 7 0 2 , 9 1 . 1 9 1 0 -0 . 0 94 1 2 7 9 , 6 1 0 .0 7 9 , 66 64 , 0 7 02.6 1 , 1 447 - 0, 181 1 28 5 . 6 20 , 0 8 1 . 7 4 63 . 0 7 15 , 3 1 , 4 6 08 -0.20 2 1 29 7, 6 2 0.0 7 9 , 65 66 .0 7 03 , 9 1 . 55 27 - 0 , 2 51 1 3 0 9 , 6 2 0 , 0 7 9 , 63 66 , 0 7 0 4 ,7 1 , 3729 - 0 ,29 0 1 3 1 -2 . 4 2 0 ,0 7 9 , 26 66 ,0 7 0 6 , 0 0 . 8 024 -0 , 1 74 1 32 7, 6 0,0 7 8 , 22 7 3 ,0 10 00,0 0, 9 0 37 - 0 . 0 36 1 33 9 . 6 0 , 0 79 , 7 7 6 6 ,0 1 000,0 0 , 9364 -0 ,0 92 1 3 4 11. 6 0 . 0 80 . 2 1 7 1 , 0 1 0 00 , 0 0 , 7749 -0 , 11 6 Cumulative Plots c vs _ N t::I CA 6 3 1:1 4 1 5 CL VS A LP HA £ VARY I NG FLA P DEF

I _ CLEAN J

o

e_

8o

_f = 3 0 ° _f=20_

0 _ - . 0 _f--z0 °

_ J ° - o ....... I | m I - ,QO ,OQ 4.0 Q B.O0 1 2 . QO' 16.00 ALPHA !

o • l !

I

NRCR B3R 4 15 CL V5 ALPHA

, V A R YING F LAP DEF

€ _ "m • m _f=30 o [_

El [!1

_ m El m

_- _f = 200

_El

rn 121

El ..:- El

6f = lO ° _ J u

El

f r--'- -- " _ a • I [] -O . 0 ! _] -4.00 O0 4 .00 O .O0 12.00 1 6 .0 0

ALPHA

.11 .

I NACA 6 3 A415 CL VS ALPHA

FLAP OEF = O. O0

(D CLEAN

IZI BIME 3

('_,I " Om

,:, 0

'_ (D

---:" 0

....I (,_)

,=, @

o_

@

-8.0 0 - 4 . 0 0 . 0 0 4. 00 8 ,00 1 2. 0 0 1 6 . 00

AL P HA

e I I 2 8 'i 'i

i NRCR 63 R415 CL V5 ALPHA

! F LAP OE F = I0 O0

•j , i

,._ (D CLEAN

I El RIME 3

q l

i o

NACR 63A415 CL VS ALPHA

FLAP OEF = 20.00

0 CLEAN

BIME 3

,G-

(!)(!)(!)

(D

,=, Fq

BI

(D

• I _ J (.J • a • m

(D °

f o !

- e . o o - 4 . o o o o 4. o o e' , o o ' z 2. oo z _. oo

AL P H A

• I !

3O / j L :i

!I NACA 6 3 A 41 5 CL VS AL P HA

i

:t FLAP DEF = 30.00

'i

i- 0 CLEAN

i

:I ZD RIME 3

o

_,-

a

o 0

• m ._J

(2) •

El

'T I u ]pr'-' . ,-,, - -,-,_ __ "- w ' u o !

-8.00 -4 . 00 O0 4.00 8 .0 0 12.00 1 6 o00

ALP H A

N A C A 63R4 1 5 C L V S ALP H A

VAR YING FLA P D E F

!,(_ G LAZE 3 I

"u

<_ <_<_

6f = 3 0 ° _" _f = 20o

<> _ . . < 3 _f =Io°

_ J ( . 3 C 3 <_> " - €: ) (: 3 • _ _ ' " , , i , - 6 , 01 _ - 4 . 00 O 0 4.00 8 . 00 1 2. 00 16 . 00

ALPHA

o • i !

3 2

i:i -

: ! - 8 ,00 - 4 .00 O0 4 ,00 8 ,00 ] 2 ,00 ] 6 O0 _!" ALP H A " i

iI °

:i } i

N R C R 63R415 C L VS AL P HA

F L AP O EF = 1 0 . O0

_) CLERN

<_ GL R ZE 3

d -

' W I m J - - 4. 00 O0 4.00 B .0g l l Z . 0 ' 0 16. 00

RL P HR

,,d - i ) . i

iil NACA 6 3 R415 CL VS ALPHA

,q

"ii 0.00

: l

_ii- 0 CLEAN

.!

i <_ GLAZE S

;i

_ F !i,i! _

ii " -

_ '_ (D(D(_

eI .I _

_ili o

i_I ..

:i _ J

:il o

t "1

:! •

.I II_ g fi _ I w ; -8. 00 -4 . 00 OO 4 . O0 O. OO 1 2. 00 16.00 RLPHR (: 3 :t

NAC F I 6 3 A4 1 5 C L V 5 A L FHR

FL A F OEF = 3 0.00

<_ GLAZE 3

I (D CLE A N

c ; "

( D

a m _ J (. J { 3 1_ ) °- 1 :3 ,,r o m

(D

o B ! | # I I I -8 . 00 -4.0 0 O 0 4. 00 8 . 00 1 2 . 00 16 . 00

AL P HA

, iP I 3 6

~1

I

j

NACA 63A415 CL VS ALPHA

:1

j

VARYING FLAP OEF

j I I "'

A. GENERIC SM~~TH

1-

j .'1 o

•

~ .

• I N ) I , o o • N A A o o =30° ID f • A

-

A o =20 ' f N A • A A

-

of=lOo ....J (J CD • A o

A •

•

,I

'I .'j I .. f ,I - 'I :1 o

r--- ,-----'----_,....----_------P"'---_

.1

-e.oi -4.00 00 4.00 B.OO 12.00 16.00

>1 '

ALPHA

~l

:I

;1 o ....

·

I

:l

d

'j

·,1 I 'I ';1

.NACA 631::1 415 CL V S ALPHA

FLAP D EF = 0.00

0 CLEAN

GENE R IC SMOO TH v GENE R IC R O U G H C_ t O

@

o @

t ' u

.. : - 0 °

( !)

._ J A ao "-

@

o @

w

@

I I ! ! ! i -O.O0 -4 , 00 O0 4 . O0 8,00 1 2,00 16 .00 AL PHA

( !)

o NRCR 6 3 R4 1 5 CL VS ALP H A FLAP DE F = I 0 . O0

0 CLEAN

'_ GENERIC SM88TH

& -

u.a" • . _ A _J ¢ J i o - • 0 -4 • O0 O0 4. O0 8 , 0'0 1 2 •O0 16 • O0 ALPHA !

, NACR 6 31:141 5 CL VS ALPH A

F L A P O EF = 2 0.00

_) CLEAN

_, GENE R IC SMOOTH

o ® - , o € - 0 .00 - 4 .00 O0 4.00 8 .00 !2 . 00 !6 . 00

ALPHA

_i cJ

. , 0 '_ _ f .!

J I o .

C _ i ! v w I I -8. 00 -4 , 0 0 O0 t t . O 0 8 .0 0 1 2 ,00 . 1 6.00 ALPHA , ,, o.

!

_ . " / - + 1 ° C vs C d

N R C R 63 R 41 5 C L V S CO

F L AP DE F = O. O0

0 C L E A N

F q R IME 3

,4 -

{:: 3

_G "

• a I

(9

,=, (!)

,,, (9

•I

.-. (9

(9

_ J

'-',::, (9 _]

o %m

e

':' (Z(D rn

• i i I • I 0 0 .0 t • 02 • 0 3 ° 0 4 . 0 5 . 0 6

CO

I 4 2

NACA 63A415 CL VS CO

FLAP OEF = O.O0

_ (9 CLEAN

_, GLAZE 3

ID o I

• , 0

- - (9

(9

_d t j

= (9 <_

(9(9 <_

o _ <3, I ! I I I I O0 .01 .02 .03 .0 4 .0 5 .06

CO

!

NRCR 63R415 CL VS CO

FLAP OEF = 0.00

(D CLERN

A_ GENERIC SMOOTH

., - v GENE R IC R OUGH

r_l" 1 :3

==

• I =ram

( D

, =, (D

-- ' ( D

( D

.._1 ( .. 3

'=' ( D

o m

(9 , a_

o ( _ v

! | | I I I O0 .O r ,0 2 ,03 . 04 . 05 . 06

CO

C vs C " I

, ,,i m _ NACA 63A415 C H VS CL

• "i VARYING FLAP OEF i : i .!

[

•_ 0 N

!!

I

I = CL

' -.4Q c _ O0 .40 80 :i • z.ao z.6o z oo • 2 . 4Q J

NRC A 63R415 CM V 5 CL

V AR Y ING F L AP D EF

" ' I El RIME 3

o "m C3 0 m

C L

-. 40 _ O0 • 4,0 • 13 0 1. ZO 1. 60 2. OO Z . 40 L- _ • I I __ I I II I

El El El

6 f=l O ° 6 f= 2 0 °

pl

= £]

e =

El 0] O]

' 6 f=30 o € 3 e q !

i ; f

NA C A 63A415 CM VS CL

Fi

! FLAP OEF = O. O0

,i

CLEAN

rq RIME 3

,i j

c }

,= CL

- . 4 0 o 0 ! 3 • 4 0 • B O ! • 2.0 !. 60 2. O0 2.. & O ! I • I I I I I I C_ .J , J

N I::ICI:I 63R 41 5 C M VS CL

FL R F O EF = 10 ,00

i

(D CLE R N

I Z ] R IM E 3

(:3 o I

C L

• 40 _ OO .€0 .BO 1.20 1.60 2.00 2 .40 1-.- .... - I __ L _ _______1 o- (_ ) I C 3 Iv 1 C 3 , d - e m .!

4 8

N(:IC(::l 63 1 ::1415 CM VS CL

FL R P DE F = 2 0 . 00

!

. 0 CLE R N I

I' q RIME 3

I

o I I o

CL

- . 4Q OQ • 4Q -_ O l . 2 !3 l. 6Q 2. OQ' 2.4Q I . I i I , I I O IIq :E.

rj m €:)

_ 5 /

N A C A 63A4t5 CM VS C L

F LA P O E F = :30.00

0 C LEA N

El R IM E 3

i { 3 ,=,,,, 4

C L

-. 4(I _ 0(1 • 40 • 80 1 . Z(I I. 60 2 . 0 (1 2 . 40 I a II J It II I , I

= r n

" (9 rq

; _ (D % m

(9 (9

(9

(9(9

{: 3

NACA 63A415 CM VS CL

VARYING FLAP OfF

o GLAZE 3

o N • o

-

•

CL

" I

g 00

.80 1.20 .40 -.40 2.00 2·40 1· 60 C N

·

I " ;1 , I i .

'I j oj CI'1 ,;1 · ,', I .';1 -I /1 ;1

J c

..

I

·

I ':1 d \1

d

, !

:,1

NRCA 63 A 4 15 CM V S CL

FLAP DEF = O. O0

i I (D CLERN .,_, GLRZE 3 , , o

"'l

B.

CL

-. 4Q _ OQ .¢Q . SO ! .2 Q | . 6Q 2. 0Q 2. 4Q .

• . i | I il I I

<)

•-" 00

¢ji :i

ii NACA 6 3 A415 CM VS CL

i.i FLAP DEF = I0. O0

._ 0 C L E A N

_, GL A Z E 3

• I . i t iq e= .!

:!

i "i

' Ck

i -. 40 OO . 40 .8 0 I - Z O 1 - 60 2 .0Q 2. 4Q i ; I " ' I I I I I I '.j

, i e) (D ( 9 <_(D

; - 0

N A C A 63 A 415 CM VS CL

FL R P OEF = 20.00

( D CLE R N

K_, GLR Z E 3

i ¢3 B a

= CL

-. , t O m . O 0 • 4 0 . B O I. _0 I• 6 0 2. O 0 2. 4 0 I • II €3

(D (D (D _ a -

p' i t 3 "

N A C R 6 3 A41 5 C N VS CL

FLAP DEF = 30.00

. ( b C L E A N

< _, G LA Z E 3

o O_ (: 3

-. 4 o _ oo • 4 o •soCL z.za z.so 2. oo z. 4 o

I f .... I I ! ,, ,I , , I , , , I C3 5 5

NRCR 6 3 R415 C M V S CL

VRR YI NG FLR P D E F

A GENERIC SMOOTH I

€3 fM €3 CL.

-. 4Q _ OO • 4Q • 8Q t. 2Q ) • 6Q 2, OO 2.4(1 I • I I I I I I _- .. 6f=10 °

z _

Z _ A I % 1 ; - _ 8f=20 0 A

AA

Z _

= A

A

. . j l_ , 6f=3 0 ° -

A

O

NACA 631:1415 CN VS CL

i FLAP OEF = 0.00

. (!) CLEAN

, _ GENERIC SM88TH

- _ GENERIC RSUGH

C :: - . , , .f ,

NRCR 6 3 R 41 5 CH V S CL

FL R F O E F = I 0.00

(D CLERN

GENERIC SM O OTH

{:} eQ D_

o C L

- .4Q o .OO . 4Q - 80 1. 2 Q | . 6Q 2 . 0Q . 2- 4Q tu_ - t I I I I I irl mm I i

NACR 6SR41 5 CM VS CL

FLAP OEF = 20 . 00

"_ GENE RIC SMOOTH

I 0 CLEAN I

o o_ c _ • I

CL

J -.4 0 _ O 0 .40 .80 1.20 1.60 2.00 2.40 I f.I J I , I | I J C ) C3 J,

N RCR 6 3 1:1 415 CM VS CL

FLA P O E F = 3 0 .00

CL EA N

A GE N ER IC SMOO TH

i 0a €_ e _

o C L

- . 4 0 0 • O 0 • 4 0 . 8 0 1 . 20 1 . 6Q 2. OO 2.4Q I ._ I I I _ I I I C3 ,ipl.e r,..) I €3

CLEAN RUN = 48

R O R t O. 6 O ,-,

P = O E F

F LA = 0.00

C L = 1. 339

CM = -0 , 0 96 ;

C D = 0.02 6 =

==

@ I"- = !

f I t -. 2 0 • t . 00

= X I C

CLERN R U N x 49

R O ll = 11.60

FL R P D E F = O . O0

CL = 1.441

CM = -0. 109

CD =

I"- !

-. 20 . • ' 0 I. . 00

= X / C

CLERN RUN = BO AOA = - , 5.40 FLAP DEF" = O. O0 CL = -0. 233 CM = -0. 045 CO = 0.011 1:) 1:) I !

1.o o o q 1 1 -.20 .20 .40 .60 -80 0 CLEAN RUN = 6 1 A0A = -2.40 FLAP D E F = 0.00 CL = 0.071 CM : -0. 047 CO = 0.010 O D !

o c) g , .

O o Q _ --,.

(= )' O o ! 1 T - . 2 0 0 . 20 . 40 .60 0

× / C

,t _ - :'_..EI:IN RU_ _, 6 2 AI3A = -0.40 FLFIP O EF = O. O0 CL - 0.3 ! 3 CPI = -0. 049 CD = 0.011 o o !

1'_1 .

Ox !

M1 tll _ .

(.._t C) I 1 T -.2[) 0 .20 .40 . 6 0 .

X / C

CL_N RI'N . : _ 63

AOa = 1•60

FLAP O E F = O.O0

CL = 0.543

CM = -0. 059

CO = 0.011

!

o o I o _ c _ ,. . LE.i::::tN RUN .... :_-_ - _"_:6: ' _4 _ ' " ..... ' _ . _

AOR = 3.60

FLAP O E F = O . O0

CL = O . 722

CM = -0. 059

CO = 0.013

I=1 !

& .

",4 o - .20 -20 -40 .60 . t.O0

× / C

CLEAN RUN = 65

ROR = 5.60

FLRP 13EF = 0.00

CL = O. 902

CM = -0. 060

CO = 0.014

f -. 2 0 ! 0 .40 1.00

o X / C

- .

CLEAN RUN : 66

AOA = 7.60

FLAP DEF = O.O0

CL = I•I00

CM = -0.076

CD = 0.017

'I

oj k O , -. 2 0 .40 l.O0

o X / C

CLEAN ffUN : 67

ROA = 8.60

FLAP OEF : O. O0

CL = I•169

CM = -0. 077

CD = 0.020

L , _ # i . , ; ,

CLERN RUN = 68

t::I O A= 9 . 60

FLRP OEF = 0.00

CL = 1 . 228

CM = -0 . 076

CO = O . 022

CLE A N RUN = 6 9

R0R = 10.60

FLAP O EF = 0.00

CL = 1 • 3 2 0

CM = -0. 09 2

CD = 0. 028

O O i ,_ ° !

D O I", , O !

r, _ ) s

' ! ""---B- __

I "'" T _ 1 .............

-.20 - X / C

\ CLEAN RUN # 70

AOA = !I.60

FLAP DEF = O.O0

CL = !•423

C H = -0.091

CD = O.O3O

I _- !

!

-.21 ) o t.O0

o X / C

CLERN RUN _ 81

ROR = -2.40

FLRP OEF = O . O0

CL = O . 088

CM ---0. 049

CD = 0 . 012

t _'; o !

o o o D 0.."

CJl o D -.20 0 .20 .40 .60 ) 0

X / C

_ ' , _ . . '. 1

CLERN RUN _ 82

ROR = -0.40

FLRP OF..F = O. O0

CL = O. "502

CM = -0. 051

CO = 0.012

!

r,_ ) I o - . 2 o ' .2 o ' .4 o .6 o .

× / C

CLEAN IRUN _ 83

A O A = I•60

FL A P DEF = 0. 0 0

CL = 0.506

CM = -0.05" /

CD = 0.013

!

o D I T _I° - . a !

D O Q _ T )

CLE R N R UN = 8 4

F L R P • 0

CL = -0.010

CM = -0. I ! 8

co=

iv}, I (3 I ' _ Ul .

!

CLERN R UN m 85

R O R = -2.40

FL R P O£F = 10.00

CL = O. 435

C M = - 0 . 1 29

C0 =

p"}.

!

O O 0 _ 1_ _ m • {,-_1 !

0 0 0 o -.20 0 .20 .40 80

X / C

0 o o

MRIN ELEME N T

FLRP

CL = 0. 346 CL = 0.0 9 0

CM = -0.07 2 CM = - 0 .05 7

- • {

CLERN RUN = 8 6

R OR = -0 .4 0

FLRP O E F = 10.00

CL = 0.669

CM = -0 . t3 2

CO -

!

CLEAN RUN = 87

ROF :I = 1• 6 0 "

FLAP D E F"= 10. O0 '"

CL = O . 9 0 8

CM = -0.14 3

CO - O

O !

O O O !

= == .

(J ! , - , !

0.

o O D O D

- ,2o . 2 o . 4o . .so

X / C oo

M R I N E L E M EN T - FLRP

CL = 0. 8 0 5 CL = 0.102

CM = -0.0 76 CM = -0.0 66

CLERN R U N = 88

R O R = 3.6 0

F LR P O E F = 10 . 00

CL = 1 . 10 6

CM = -0 . 1 4 2

= CO =

I I,o. I, i@ .

I I !

-.2 o • . eo oo

o X / C =

, = X / C ,.. - _

MR IN ELE M ENT " ' FLRP " -

C L = 1. 0 0 2 CL = O. 1 0 3

C M = - 0 . 0 75 C M = - 0 . 0 68

CLEAN RUN _ 89

AOA = 5.60

FLAP OEF = 10. 0 0

CL = I•220

CM = -0. 133

= CD =

!

-. 2 0 8 0 O0 0 o

o X I C o X I C

M A IN EL EM E NT F LA P

CL = 1.111 CL = 0.10 9

CM = -0.0 6 1 CM = -0.0 7 2

CLERN BUN = 90

ROR = ?.60

FLRP OEF = 10.00

CL = 1.354

CM = -0.136

CO =

I 00. 0=.

t t '_ . 1 ,10 .

I I 0_ o ( - , 1 o o =, .

I !

-.2 o o o x / c _ o __ oo

" M R IN E LEM E NT " FL R P

CL = 1 .24 1 CL = O. 1 13 "

CM = -0. 060 C M = - 0. 07 7

CLE R N RU N = 9 1

R O R = 9.6 0

F LR P O EF = 10 . O0

C L = ! .526

CM = -0. ! 53

CD =

p - $ I • i

CLEAN RUN = 92

AOR = II•60

FLAP OEF = I0.O0

CL = I. ' / 30

CM = -0. I'/8

CO =

f.,l! I o &, 3 D ° o.

-.20 o 80 O0

o X / C

MRI N ELEMENT FLRP

CL = 1 .578 C L = O. 1 52

CM = -0 . 0 7 1 CM = -0 . 1 0"7

CLE A N R UN = 93

R OR = 1 2.6 0

FL A P DE = 1 0. O0

CL = 1 . 71 5

CM = -0. 17 8

o CO =

o !

o lb . I D .

I I -.20 80 O0 o o

o X / C = X / C

" M A IN ELEME N T " FLA P

C L = 1 .557 CL = O . 1 58

CM = -0 . 0 65 CM = -0 . 11 3

CLE R N R UN = 94

R O R = 13.60

FLRP O E F = I 0 . 0 0

CL = 1.823

CM = -0. 196

CD =

_.

!

-,20 )0 80 O0 0 o

= = X / C

" M R IN E L E M E NT " FL R P

C L = 1 ,666 CL = 0 ,. 1 57

CM = -0 .08 2 CM = - 0 .1 14

CLE R N R UN = 95

ROR = - 6.4 0

FL R P O E F = 20 . O0

CL = O . 4 2 6

CM = - 0. 21 9

C0 -

-

I -_- D D I I 0 o 0 o -,20 .20 .40 .80 ,80 1.00

× / C

0 o D 0 ell

M R I N E L E M EN T " " FLRP

CL = 0. 263 CL = O. 1 63

CM = -0. 10 9 CM = -0.11 0

CL ERN RUN = 96

R O R = - 2.4 0

FL R P DEF = 2 0 . 00

CL = 0 .894

CH = -0 .231

o C 0 =

I

o

MRI N E L E M EN T F L R P

C L = 0.724 CL = 0 . 1 69

CM = -0.11 5 CH = -0.1 1 7

CLE RN RU N = 98

RO R = 9.6 0

FLRP O E F = 20 . O0

CL = 1 . 87 1

CM = -0.2 5 5

=0 CO =

I _ .

!

=0 ..

U_ . I D .

I I -.20 .80 t.O0 0 o O D

" HRIN ELEHENT " FLRP

CL = 1.668 CL = 0.203

C H = -0 . 1 0 0 C H = -0 . 155

CLEA N R UN = 99

A O A = 3. 6 0

FLA P O E F = 20.00

C L = 1.4 6 3

CM = -0.231

CO -

I

°

0 _ o { Jo D -. , o ! ,- .

!

- , 20 o 80 O0 o X / C € ,

M R IN E L E M E N T "

FLA P

C L = 1 . 2 9 5 C L = O. 16 8

C M = - 0 .I!I C M = - 0 . 120

CLERN RUN = I00

ROR = -10.40

FLRP OEF = 30.00

CL = 0.308

CM = -0.288

C0 =

@ !

0 _ 0 0 D D - .20 -20 .40 80 .80 ! 0

X / C X

0 0 D D

" M R IN ELE M E NT " F LRP

CL = 0 . 10 8 C L = 0 .2 0 0

CM = -0.1 44 CM = -0.1 4 4

• t

CLE A N fl UN = I01

R O R = - 6. 40

FL R P D E F = 30.00

CL = 0. 797

CM = -0. 30 5

CD =

I 0 0 0 0 I I D e l

" M R IN ELE M E N T " F LR P

C L = 0.58 0 C L = O. 2 1 8

CM = -0. 14 6 CM = -0. 1 59

-~

CL E RN R UN ,s 10 2

R O R = -2. 4O

F LR P D EF = 30.00

C L = 1 • 229

C M = - 0 . 304

C D =

I

o

• { ' _ l J , e I 0 0

" M R IN ELEMENT F L R P

CL = 1 . 025 CL = 0 . 204

C M = -0 . 1 50 C M = - 0 .1 53

,2 L ................ ............

CLEAN RUN # 103

B O A = 1.60

F LAP OEF = 3 0.00

C L = 1o7 4 1

CM = -0. 3 1 8

o CO =

I •80 O0 - .20 o ° X / C € , {:

" M R I N ELE M ENT " L RP

CI . = 1. 5 1 3 CI . = 0 . 228

C M = -0 . 14 2 CM = -0 . 176

CLEAN RUN u 104

AOA = 5.60

FLAP OEF = 30.00

CL - 1.917

CM = -0.311

CD = --_ .. _-

o o • ,...

I o o c c • • II) VJ I I \0 0\ C

•

I

"

0..

U o c •

- I

-.20

c

x C

o •

-

MAIN ELEMENT

FLAP

CL = 1.695

CL = 0.222

CM = -0.130

eM = -0.182

• $

C LEA N RU N = 105

R O R = 9 ._0 30

F L A P DEF .00

C L : 2. 10 7

C H : -0 .328

C0 =

I

=

I - °20 . 20 o .80 80 O0 O D D line

MAIN ELEHE N T FLA P

CL = 1 , 8 79 CL = O . 228

CH = -0. 1 27 CH = -0 ,20 1

CL EA N R UN = 10 6

R O R = t O. 60

F LA P DE F = 3 0.00

C L = 2 . 276

CM = -0. 35 0

- C O --

r ,, .

I ! I g

° == . °

Q . . t' _ . I f ) (.11 -.20 80 O0 0 0 o o ea

" M AI N ELE M E NT " LA P

CL = 2. 0 43 CL = 0 .233

CM = -0 . 140 CM = -0. 2 0 9

C L ERN RU N = 10 7

RO R = 11 .60

F LRP D EF = 3 0. 00

C L = 2 .1 74

CM = - 0 . 347

CD =

0=

r, w.

i °

I ' _I_ .

_,_ '_ _ , I -. 20 o I0 ZO 80 O0 o o o

M R IN ELE M E NT - F LR P

C L = 1 ,935 C L = 0, 239

CM = -0, 128 CM = . -0 , 2 19

i.

C LERN R UN = 135

R O R = 1 3.6 0

FLRP DE F = 10 . 00

C L = 1 .79 1

CM = - 0. 1 25

= CO =

o I

C LE R N R UN = 1 36

RO R = 1 4 . 6 0

FL R P OE F = 10 , 00

CL = 1 ,8 02

CM = -0 , 1 34

C 0 -

I G- o ( ,-II o ! I

, _ 0 ° ° ,0 e 0 __ 0 0

• i

" M R IN ELE M E NT " " FL R P

C L = 1. 66 1 C L = 0.1 4 1

C M = -0 . 03 1 CM = - 0. 1 03

,

RUN. 137

CLEAN

AOA = 11.60

FLAP DEF = 20.00

CL = 1.955

CM = -0.209

CD = -_ ... _ .. -

o I:) • ,...

I I:) o I:) I:) • • In

If

I t-' I:) 0 C) I:) N • • . \ t') Q..t') , l

u

Q..

(.)0 I:) D

•

• ..

..

, I

-.20

I:) o ... ~os;; ...

FLAP

MAIN ELEMENT

CL = 0.168 CL = 1.787

CM = -0.132 CM = -0.077

CLERN RUN = 1 38

RO R = 12 . 6 0

FL R P D E F = 2 0 , 00

CL = 1 . 97 2

CM = -0 , 20 8

° C O =

!

°

0 ° I

C L ER N R UN = 1 39

R O R = 1 3 , 6 0

FL R P DE F = 2 0 . 00

C L = 1 ,928

C M = -0 , 2 1 3

m

CO -

D o I f_ , I = . = .

= ,. _ ,.

IL o t , -- ) D o = .

-.2o _ .8o oo

e,-a,

HR]N ELEHEN T FLRP

CL = 1,755 CL = O 0 173

CH = - 0, 0 73 C M = - 0. 1 40

f ' :' ." ;.

L

RIHE 3 R OUGH RUN a ?6

ROA = -2.40

FLAP OEF = O. O0

CL = O. 054

CM = -0. 054

CO = 0.016

!

l%l .

o t.n -. 20 0 "r.20 'r. 40 • 60 0

X / C

R I H E 3 R OU GH R UN = " / 7

R O R = -0.40

F L R P DEF = O . O0

CL = O. 346

C H = -0 . 0 59

C 0 = 0.01 4

o !

T r -.20 .2 0 .4 0 .6 0

X / C

_ e

R I H E 3 R OUGH R UN . ' $ ' 78

ROA = 1.60

FLAP DEF = O . O0

CL = O. 521

CM = -0. 049

CD = 0.015

!

i ' l l.

I -' I o L ! !

- .2 0 .2 0 .4 0 .6 0 O 0

× / C

RIME 3 ROUGH RUN ,s "79

R O R = 3.60

FLRP OEF = O. O0

CL = 0.747

CM = -0. 049

CO = 0.01- /

!

N = i- , !

oo

- '. 2 0 . 4 0

X / C

R I M E 3 ROUGH RUN = 8 0

R OA = 5.6 0

F LAP O E F = O . O 0

CL = O. 933

C H = -0 . 0 46

CO = O , 0 2 1

!

- '. 2o oo . 4 o • t.o o

X / C

RIME 3 ROUGI-[ RUN _ [59

ROA = - t O, 40

FLFIP OEF = 30, O0

CL = -0,03 7

CM = -0. 209

o CO =

e O r3 .

I I

H R I N ELEHENT " FLAP

CL = -O. t51. CL = O. tt4

CH = -0. t 28 CH = -0.08 t

R]HE 3 ROUGH RUN " 160

ROA = -6,40

FLAP DEF = 30,00

CL = 0,700

CH = -0.287

CO =

o I

& •

! !

8_ ! !

-,20 0 .20 .40 80 1.00

X / C

HA]N ELE H ENT _ FLRP

CL = O , 5 tt CL = 0 , t 89

C H = -0 , t 48 CH = -0, t3 9

RIME 3 ROUGH RUN _ t6t

ROA = -2.40

FLAP DEF = 30,00

CL = t.t94

CM = -0,296

00 =

D €4.

I

"' MRI N ELEMENT " ' FLAP

CL = O, 988 CL = O, 206

CM = -0. 141 CM = -0. t55

_- ,J

RIME 3 ROUGH RUN = 162

ROR = t,60

FLRP DEF = 30,00

CL = t,669

CM = -0,295

CO =

!

f 1 -,20 8O t.O0

X / C o

MRIN ELEMENT FLRP

CL = 1,463 CL = 0,206

CM = --0, 133 CM = -0, 16 l

_-_..

i . \

R.IME 3 ROUGH RUN =' 1.63

AOA = 5.60

FLAP DEF = 30,00

CL = 1.971

CM = -0,274

C0 =

p-.

!

I !

n ' 20 • O0 80 : _ •

X I C

' ' ' __E_' O0

MRIN ELEMENT FLAP

C L : 1.768 CL : 0,204

CM = -0,106 CM : -0,168

R]HE 3 ROUOH RUN - 164

ROR = 7,60

FLRP OEF = 30,00

CL = I • 921

OH = -0,239

o CD =

I -.20 O0 80 t O0

HR[ N ELEHENT '-' LAP

CL = 1 .7 28 CL = O . 193

CH -- -0,071 CH - -0, 168

J

RIHE 3 ROUGH RUN . 165

F IO R = 7.60

FLAP DEF = 20 , 00

CL = 1 , 7 50

C H = -0 , t 90

CO =

r ' - I o o i !

0 - !

r

20 oo ' e o _,_oo

X / C

j eg -xTc

HR I N ELEHENT " FLRP

CL = t. 592 CL = O , t 58

CH = -0 . 068 CH = -0, 122

. - •.... . . _" ...... _::_- . : : :1 .. ." : : .' ............ . .__ ........ -. " __ .L .. :. _ z.¸- ....... _ .... - .i . ......... _ _ .... _ ...... " .... :_. . _ . _ __ ii___. _ .-. _ -:".

RIME 3 ROUGH RUN . 166

ROR = 9.6O

FLRP DEF = 20.00

CL = 1.752

CM = -0.173

CB =

I ! 1 -.20 O0 80 O0

o C

MRI N ELEMENT " FLRP

CL = 1. 596 CL = O. 156

CM = -0,051 CM = -0, 122

RIME 3 ROUGH RUN u 167

AOA = 8.60

FLAP DEF = 20.00

CL = 1.704

CM = -0.176

CD = ------

o o • r-- I • an I .....

.....

• (') 0- I W 0- W o • I

-

-.20

o o

lC

x/c

·

...

FLAP

MAIN ELEMENT

CL = 0.161

CL = 1.543

CM = -0.124

CM = -0.052

RIME 3 ROUGH RUN . 168

ROR = 6.6O

FLRP DEF = 20.00

CL = 1.670

CH = -0.190

CO =

I I :::) I_ ,__ ,4.

I !

O _ t -. ) c _ !

m I r 20 O0 _ 80 O0

X I C o'='

MRI N ELEMENT '- ' FLRP

CL = 1 .5 1 0 CL = 0.160

CM = -0 . 07 1 CM = -0. 1 20

4 . % .

R IHE 3 ROU G H RUN # t 69

AOA = -6.40

FLAP DEF = t O. O0

CL = -0. 0 73

CH = -0. t t O

_, CO =

I I * n - m -_ 2 0 r 2 0 . r40 . • .e O .00

X / C X / C

o e a

HAIN ELEHENT " FLAP

CL = -0. 14 2 CL = O. 069

CPI = -0 . 066 CM = -0. 044

4,%

RIME 3 ROUGH RUN _' 170

A O A = -2.40

FLAP OEF = I0.00

CL = 0.418

CM = -0.120

CD =

o I ! !

0_.

(..)

r r -.20 0 .20 .40 . .@0 O0

X / C

MRIN ELEMENT " FLAP

CL = O. 337 CL = O. 081

CM = -0. 068 CM = -0.052

\... .

R I M E 3 R OU G H R UN == t' 7 t

RO R = t . 6 0

FL R P DEF = 10.00

C L = 0.890

CM = -O. tt6

CD =

J I M

" MR IN E L E M EN T F L R P

CL = 0. 791 CL = 0.0 99

C H = -0. 0 52 C H = -0. 0 64

%.

RIME 3 ROUGH RUN # 172

AOR = 5 . 60

FLAP DEF = 10 . 00

CL = 1 . 216

CM = -0 , 109

CO =

I

RIME 3 BOUGH BUN _ 173

AS R : 7,6 0

FL A P DEF : I0.00

CL : 1,393

CM = -0, III

CD : _.

!

I ! !

-,20 eO C)

X / C _ X / C

MRIN ELEMENT " FLRP

CL = I, 277 CL = O , 116

CM = -0.032 CM = -0.078

R!ME 3 RO U G H RUN == 1 7 4

R O R = 9. 60

F LR P D EF = t O . O0

C L = t.4 24

CH = -0 . 088

co =

I t . J_ = , ,llI

X / C eo oo

M R IN ELEMEN T ,-,

F LR P

CL = I, 2 9 9 CL = O. 125

CM = -0 . 002 CH = - 0 . 0 87

RIME 3 ROUGH RUN . 175

AOA = IO.BO

FLA P DEF = I0.O0

CL = 1.516

CM = -0.098

CD =

P-.

!

o

I I

; 0_, • T ¸' _ ( 1 _ ( -. ) _ o.

!

-'= o oo x / c 8 0 _ J- __ x / c -oo

MAIN ELEMENT FLAP

CL = 1 .3 9 2 CL = O. 1 2 5

CM = -0. 011 CM = -0. 087

RIME 3 BOUGH RUN _ I76

R O R = 11 . 60

FLRP DE F = 10 . 00

CL = 1.480

CM = -0.093

CO =

I O _ f.JD I' -.2 0 OO . 80 _0 0

X / C _j _ X / C

MRIN ELEMENT " FLRP

CL = I.355 CL = O. 125

CM : -0.005 CM = -0. 088

GLAZE 3 RSUGH RUN : 71

AOA = -2.40

FLAF DEF = 0,00

CL = O.082

CM = -0.050

CO : 0.016

0 "#° !

Oo -.' 2 0 0 r. 20 T. 40 - 60 .

× / C

GLAZE 3 ROUGH RUN : 7 2

A O A = -0.40

FL A P D E F = O, O0

CL = O. 3 0 6

CM = -0.05O

CO = 0.015

03,, !

I- - ' ( '_1o _ 0 - . 20 '0 _20 .4 0 . .6 0 . O0

X / C

GLAZE 3 BO U G H RUN = 73 f

ASA = I. BO

FLRP OEF' : O. O0 CL = 0.528

CM = -0.040

CD = 0.016 Q (v,#.

I !

-.20 .20 .40 .60 .

X / C

" , _ , .

I

GLAZE 3 ROUGH RUN : 74

ASA = 3.60

FLAP DEF = O.O0

CL = O . 752

CM = -0. 044

CD = O. 023

!

€ -.20 -20 . 4 0 . 6 0 l. O O

X / C

l

GLAZE 3 ROUGH RUN : 75

AOA : 5.60

FLAP OEF = O.O0

CL = O.893

CM : -0. O 2 5

CO : O.O3 2

!

-. 2 0 . 40 - 1 . 00

X / C

G LRZE 3 R OUGH R U N = 1 4 0

R 0 R = - 6.4 0

F LR P OEF = l O . O0

C L = -0 . 0 55

CM = - 0. I1 8

CO = --

O O _o !

_ O c_ o

_.J, T"

O D

.._ o x , c . , o . . ,o !_. oo

o D e _

M R I N E L E M ENT " F L RP

CL = - 0. 1 26 C L = 0 .07 1

CM = - 0 . 0 " / 3 CM = - 0 .0 45

GLRZE 3 RO U GH R U N =_ 1 4 1

R O R = - 2.40

F L R P OE F = 10 . O0

CL = O . 388

CM = -0 . 1 23

_ . CO =

'7,"

N ° t _ ll .

I I p a L_ D 0 i • € .,)1 !

O D -.20 10 .20 .40 . 80 O0

X / C

o D

MAIN E L E H ENT " FLA P

C L = 0 .3 0 3 CL = 0 . 0 85

C H = - 0 . 0 69 C H = - 0 . 0 54

GLRZE 3 R OUGH RU N = 14 2

R O R = 1, 6 0

FL R P OE F = 10 , 00

CL = 0 .89 1

CM = -0 . 10 8

C 0 =

D o _= I tj l _ • I | Q.

t . . .t o o • 40 80 O0

- .2o . _ Ox / C

°

HR I N ELEMENT " FLRP

CL = 0 ,791 C L = 0,099

C M = -0 . 0 45 C M = -0. 063

, , €

G LA Z E 3 R O UGH RUN = 1 43

AO A = 5.6 0

FL A P DEF = 10 . O0

C L = 1 . 23 5

CM = -0 . 0 94

CD =

o

IP',.

I Q I !

IL t , .l o 0 .

T

-.=_ 0 = X / C " oo g . _ X / C .00

MAiN ELEHE N T " F L A P

CL = 1, 1 31 C L = O , 1 0 4

C M = -0 , 0 25 C H = -0 . 0 69

• t , •

GLRZE 3 R OUGH RUN = 144

ROR = 7 . 6 0

FLRP DEF = 10 . 00

CL = 1. 3 4 6

CM = -0.0 89

CD =

I 0 € : J 0 o IJ _. It J l= I !

GLAZE 3 ROU GH R UN = 1 4 5

R OR = 9 . 6 0

F L A P DEF = 10. O0

C L = 1• 389

CM = -0. 0 89

CD = ......

o r : I D

°

u' J !

I GLAZE 3 ROU G H RUN = 146

AOA = 10.60

FLAP OEF = I0.00

CL = 1.431

CM = -0.11 7

_ . C 0 =

I

o

! I _ D U w \ o .

I • .8 0 t . 00

- . 20 o X / C

MAIN ELEME N '[ " FLAP

CL = 1 . 3 00 CL = O , 13 2

CM = -0 . 026 CM = -0 . 092

OL F IZ-E 3 ROUGH RUN = I47

AOA = 11.60

FLAP DEF = I0.O0

CL = 1.419

CM = -0,148

,8 co=

,.:.

I I I _4 f ._ ) l I 0_ (' - ) o t .= e °

- 2 0 o X / C o t. oo

o

'. • . . oo _ '

MRI N ELEMENT "' FL R P

CL = I.2 76 CL = Oo 14 3

CM = -0.047 CM = -0,101

G LRZE 3 ROUGH RUN ,: 148

ROR = 7.60

FLRP DEF = 20.00

CL = 1.720

CM = -0.167

CD =

I i' T -.20 80 O0

X / C o o

MRI N ELEMENT "' FLRP

CL = 1 • 559 CL = O . 160

CM = -0 . 046 CH = -0.12t

l

GLRZE 3 ROUGH RUN =, 149

AOA = 9 , 6 0

FLAP OEF = 20 , 00

C L = 1. 6 81

CM = -0 , 20 3

CD =

:5

r :.

I o o

G , . J , -

I !

GLRZE :3 ROUGH R UN . 150

AOA = 8.60

FLAP DEF = 20.00

CL = 1.664

CM = -0.174

CD =

I o_ t ...J _ B ,w - 4 .

!

-_20 . 00 1 80 t . 00

X / C o

o / C

MAIN ELEMENT

FLAP

CL = 1 . 504 CL = 0 . 160

CM = -0.049 CM = - 0.125

G LRZE 3 ROUG H R UN = ! 5 1

ROB = 1 0.6 0

F L RP DE F = 2 0 .00

C L = 1 . 6 61

C M = -0.244

C0 -

I (Jo O I -.20 O0

= X / C o X / C

im e

HRIN E L EHE N T F L R P

C L = 1. 5 0 4 C L = O . 177

C H = -0 . 100 C H = -0 ,143

............................... ,, ..... • ........... z . .....

GL R ZE 3 ROUGH RUN = 152

R O R = 6.6 0

F L A P OE F = 20 . 00

C L = 1 . 6 65

C H = -0. 16 3

C O -

I

GL R ZE 3 R OU GH RU N = 1 53

RO R = - 6 .4 0

FL R P OE F = 3 0 . 00

CL = 0 .696

C H = -0 . 288

o C 0 =

o e I

o ==

t '_ l, 0,1.

I I

-._ o _ o " _ / c " .8 o = ° oo

" H RIN ELE M ENT _ FLRP

CL = 0 .5 0 9 CL = 0 .187

C H = - 0 .148 CM = -0 .14 0

G L RZ E 3 R O UGH RU N = 1 5 4

R O R = - 2.4 0

F L R P DE F = 3 0 . 00

CL = 1 .2 1 2

CM = -0 . 289

C 0 =

I

° ==

N- N- I I o O

MRI N ELE M EN T F L R P

CL = 1 .0 1 2 C L = 0 .20 0

CM = -0 . 1 36 CM = -0 . 1 53

GL RZE 3 R O U G H R UN = 1 55

R O R = 1 .6 0

F L R P DE F = 3 0 . 00

CL = 1 .648

CM = -0 . 2 77

C O : o I - .20 .co oo o

X / C =

HR IN E L E M E NT FL R P

C L = 1 .456 CL = O . 1 92

CM = -0 . 1 2 5 CM = -0 . 1 52

GL R ZE 3 BOUGH BUN = 1 56

RO B = 5.60

FLRP DEF = 3 0. 0 0

CL = ! • 934

CM = -0. 2 50

CO -

r "-.

I

° ==

w , I t _ .

! m (. 3 o !

-.20 O0 80 O0 o

H R IN E L E H E N T " F LR P

CL = 1 .745 CL = O . 1 89

CH = -0.09 2 CH = -0. 158

GLRXE 3 RO UG H R UN = 157

ROR = 7 .60

FLRP O E F = 3 0.00

CL = 1• 96 3

CM = -0. 261

C0 -

r "-.

I I _. 1 4 !.

I I -.20 .00 80 o O0

X / C =

HRIN ELEHENT FLAP

C L = 1.763 CL = 0.200

CH = - 0 ,0 8 7 CH = -0. 174

_ ..° • !

GL RZ E 3 R OUGH R UN = 158

ROR : 8 . 6 0

FLAP O E F = 3 0,00

CL = 1. 9 0 3

CM = -0 . 2 7 7

C0 =

o I O0 -.20 O0 80 o

X / C =

HR IN ELEMEN T FLRP

CL = 1 , 700 CL = 0.203

CH = -0 , 094 CH = -0 , ! 83

GENE R IC R OUG H R UN = 50

R O R = -2 .4 0

• F LR P D E F = O . O0

CL = O . 0 55

CM = -0 . 0 6 0

CD = O . 0 34

e !

== .

L ' _ I ° I-' !

U't t O , ' 20 O0 . 2 0 "T 40 1 60 80

× / C

|

G E N E.R. I ' r .. B O U GH R U N = S ' I

A OA = -0.40