Document
REPORT NO. 732
.
PRESSURE DISTRIBUTION OVER AN NACA 23012 AIRFOIL WITH A FIXED SLOT AND A SLOTTED FMP By THOU A. Eums and JOHN C?. Low-m m SUMMARY (references 2 and 4).
This type of sIot is advantageous b~ause it produces little increase in drig at high+peed A pmwurdistrhdhn inueetigation w conducted in conditions and is more effective than the fixed slot, but tlw LM& 7-by iO-foot wind tunnd to (ktermine the air its construction and operation offer difFLcuMes.
lode on an iVACA %OM airfoil in combination with a The present investigation inoludes load data for the j%cedLmding+?dge tdot and a 8~otted$ap. Prewures were optimum fixed-slot arrangement reported in reference 1 measured mer the upper ad lower eurfirms of th4 mn- and for a slotted flap on an NACA 23012 ,airfoil.
pon.mt parik of the oombi&n for semwl angk8 of APPARATUS AND’ TESTS a.t!ack and at wvemljlap 8ettiqJ8.
MODEIS % G%@ presented a8 ‘premure diagra?n8 and graphe The airfoil model used in these ksts had a 7-foot of mtion coejicienti, are applicable b m-b, dizt, and $ap span and a 3-foot chord; it conformed to the NACA designs for the combinai%m. The data ~howed the fii- 23012 airfoil profle (table 1) and was constructed of %ng: % peak pre88ure8 d the no8t?Of h 8kt and the kminated mahogany, with a‘ hollow section to accomm- ‘ I?oadeon the 8.hI# were higher in thi? angle-of-atiaok range odate the capper pressure tubes. The basic model where 8kIte art? uaefd thun @e peak pre%urea and the mnsisted of the airfoil in combination with a full+pan hnzde S* in preuiouely pwblished data on the Handky h Page type of 8tot. The kmi=8 on the 8k#ted $ap 8hmoed only a 8@ht chunge un”thth% addition of a kaxhg-edge 8kIt, and d is belimed thd any conoentimd $ap woufd 8how dy a 8@ht change in kmding if incorporated with “:~rl ajxe.d leading-edge 81oL .
.—. — INTRODUCTION ... ‘.
-.’.-’..
--’ The National Advisory Committee for Aeronautics has undertaken an extensive investigation of air Ioada ““m Q “256(5C m- on high-Iift and stall-prevention devices to obtain data &“ useful in the design of safer airphmes. With the in-
l-l
.MOc crease in wing loakg and the use of highly tapered FIGG”RB L-Crwd sedkm of modd shodng a&foI140t4.lap combinatkm used In pmmnm-dktdbution task , wings, some device is necessary to improve the stalhng characteristics of the wing. There are several ways fixed Iedng-edge slot. and a full-span dotted flap in which these unadmirable oharaoteristica can be (fig. 1). The M slat was attached to the airfoti by improved. One method now being employed is the four thin mettd fittings and the slotted flap was at- addition of a leading-edge slot to the tip section of tached to the airfoiI with tbxee metaI hinges.
the wing.
The full-span leading-edge sIott(fig. 1) was daveloped The simpkt kading-edge slot to construct and by the NAC.A and is designated now 11, slat 5C in operate is the &d slot described in reference 1; in referenoe 1. The SIat has a chord of 5.940 inches this me the SIatis an integral part of the wing. This (16.50 peroent of the over-aU airfofl chord). The type of slot has the disadvantage of increasing the drag trsiling+dge portion of the slat was constructed of at the h~h-speed condition but may be advantageous a.huninumso that it maintains ita shape under load.
where ruggedness and simplicity of construction are The fuhpan aIotted flap (table I) was developed by essentiaI. the NACA and is designated 2–h in reference 5. It Two types of movable leading-edge slot are the has a chord of 9.238 inches (25.66 percent of the over- HandIey Page (reference 2) and the MaxwelI (reference SU airfoiI chord). The path of the flap nose (table I) 3), whioh are fornied hy the movement or rotation of is the optimum one repcn-ted in reference 5. The flap the SIat with respect to the main airfoil. Some load was arranged for looking at downward, or positive, data are available on the Handley Page type of slot flap deflections from 0° h 60° in 10° increments.
REPORT NO. 7i3%NATIONAL ADVISORY COM-idlTTEE FOR AERONAUTICS TESTB The model was fitted with a single chordwke row of The teeti, except for those at large angks of attack prcwsnme orifices 21 inches from one end of the airfoil and located along the chord as shown in table II and in which the dynamic pressure was lowered as much as @ure 1. Tubes leading from these ofices were 19 percent, were run at an average dynamic possum of 16.37 pounds per square foot. The decrease in brought out ihrough one end of the wing (fig. 2) and dynamic pressure was necessary to measure the peak connected to a dndtiple-tube manometer that records pressures because of limitations in the manometer.
photographically.
The average dynamio pressure, 16.37 pounds per square foot, corresponds ta a tunnel velocity of 80 miles per hour and a test Reynolds number, based on
i!
the chord of the airfoil with flap retracted, of 2,190,000.
Because og the turbulence in the air stream, the cfTec- tive Iteynolds number was 3,500,000. (See reference 6.)
The modeI was tested with the sIotted tip deflectid from 0° to 60° in 10° increments. Teste were made at each flap deflection through an angle-of-attuck rango from about zero lift to approximately maximum lift in l 4° increment.a. With the model at a given angle of attack and flap setting, time was allowed for the tunnel and for the manometer to become stable before tho pressureawere recorded.
r“” v;--’ 7
I PRESEFJTATION OF DATA
I )
PEIWSUItE DIAGItAMS Ill All the diagrams of pressures over the upper and lower surfaces of the airfoil-elotAlap combination me given as pressure coefficients P where p=?
and I g statio pressure at a point on airfoiI POstatio pressure in free air stream q dynamic pressure of free air stream .- Pressures over the airfoil with the fixed slot are shown in figure 3 and pressures over the airfoiI with tho fixed slot and the slotted flap are shown in figuroa 4 to 10. A comparison of the loads on the pIain airfoil ;:; 1$ 1 1.1. I \ with the loads on the slotted airfoil is shown in figure
~, ill ‘]/’2”
11, and a comparison of the loads on the pIain airfoil Vertical sectian with slotted flap with the loads on the slotted airfoil
v
with slottad flap is shown in figure 12.
flow tests In tha 7-by M-foot FIGUEX 2.—Morlel fnatallatlon for two—dhmhd whd ~umeL In figures 3 to 10 the pressures over the main airfoil TEST INSTALLATION and the slat are plotted normal to the airfoil chord and the pressures over the slotted flap are plotted normal The model was mounted in the closed test smtion of to the undeffeoted flap chord line. In order to prevent ‘ the NACA 7- by 10-foot wind tunnel (reference 5).
overlapping of the component parts of the combination Because the model completely spanned the tunnel and to keep the mrves as Iarge as possibIe, the slat was except for small clearances at each end (fig. 2), moved forward and the &p was moved rearward fmm approximately twc-dimensional flow was obtained.
The pressures are plotted for the normal positions.
Torque tubes attached to the balance frame held the the component parts in the positions shown by did model rigid and aIsc served as conduits for the pressure lines. The norrmd positions of the slat and the flap tubes. The angle of attack was set from outside the are shown by dashed lines. The pressures over the tunnel by rotating the torque tubes with a calibrated main airfoil and the slat for &urea 11 and 12 are electric drive.
PRESSURE DISTRIBUTION OVER NACA 23012 ~IL WITH FIXED SLOT AND SLO’ITED FLAP pIotted normal to the airfoil chord, and the pressure nt normal force on slat clone over the slotted tip are plotted normal to the deflects{ Z* chord force on shit alone flap chord line. The position of the component pati m pitohing mommt of slotted airfoiI with flap in these figures is normal. ?nf pitching moment of flap alone “ m% COEFFICIENTS pitching mommt of slat aIone a’bout Ieading edge of sIat, due b normaI force The prassure diagpmns wme mechanically integrated m,= pitahing moment of slat aIone about chord to obtain data hmn which standard nondimensional Iine of slat, due to ohord force section coe.flicients were computed. Where the tam “fip done” or “&t done” is used, it refers to th c chord of airfoil with flap neutmd Cf chord of sIot&d flap (over-alI Iength of flap) forces and the momente on the flap or the slat in the c, chord of s~at (projected distance along airfoil presmce of the rmt of the airfoil-slokflap combination, chord Iine) (See f3g. 1.)
The section coefficients are de&ed as folIows: and norrnaI-force coe%icient of slotted airfoil with flap (n/gc) angIe of attack for Mnite aspect ratio Q% 6, angIe of flap deflection normal-force codliciant of flap alone (?bJqcJ . . .
With the exception of the chord-force moment of the normal-force coefficient of slat alone (nJgc,) sIat, the coellkiante for the combmtion w~e derived chord-force coefficient of slat aIone (z,/qc,) from the norrmd forces alone, the chord force of the flap resultant-force coefficient of slat alone being negkted. Negkcting the normal-force mm- ponent of the chord force on the flap in cakulatiom for (d&x) the combiition reduced the normal-force c03flicients pitching-moment coefficimt of slotted airfoil by a maximum of approximatdy 0.08. Because the with flap about quarter+hord point of air- drin fiction of the flap wilI enter into any cmreotion foil (m/g&) Eorthis discrepancy, no attempt was made to include pitching-moment coeilicient of flap alone about ~ correction for flap-chord force in, the &al resuk quarter-chord point of flap (mJgc~ bmnmch as the modeI mmpletdy qpanned the jet, pitching-moment co*cient of normal force tie integrated rcmdtsj which are in coefbient form, of skt aIone about leading edge of sIat may be used as section characteristics.
(?n%/qc,q “ Figures 13 to 16 show the section characteristics of pitching-moment coefficient of chord force &e combination, of the slat alone, and of the flap aIone.
of s~at done about h?ading edge of dat Figure 15 shows n vectorial representation of the (?nrjgc:) xxuikant-force coeflkient on the sIat alone.
pit&ing-moment coefficient of slat aIonc PRECISION about leading edge of slat (c.z~+cm%) Experhmmt.al errors in the results presented in this Centeraf-pressure Iocation of slotted---airfoil “eport are bdieved to be within the followirg Iimits: tith flap in percent airfoil chord bxnn Iead- ?-_______ i&_________________________ &2 percent ing edge of airfoiI +1 percent [------------------------------------ [(”’’-%)x’””] Ao.l” %------------------------------------------ centm-of-pressure location of flap al&e in if____________________________________ &“.50 perrent flap chord from Iea@g edge of flap The normaI-force coefficient of the combination was mrected as expIained in refmace 5. This correction
[o’’-:)x’””l
:ends to reduce the magnitudes of the pressures; the center-of-presum Iocation of slat aIone in resultsfor the &t and the flap, which me uncorrected, percent sIat chord from Ieading edge of sIat hould be conservative.
c= DISCUSSION –=X1””) l G4=
( SECTION PBESSUItE DISTEISUTION
The pressure curves (figs. 3 to 10) show the distribu- center+f-premure Iocation of slat aIone in tion of pressure over the upper and lower surfaces OF percent slat chord above chord line of sIat he airfoif for various combinations. These curve9 nay be used for deai@ng of ribs, slats, and flaps as wII as for showing the change in distribution as the Iap is deflected. In general, th~e curves show that normal force on slottd airfoil with flap he fixed slot has little effect on the net pressure dis- normal force on flap alone normaI to chord of tribution except that it maintains flow above the stall flap ange for the plhin wing.
mM90-4s-7 ___ Chord line..
..@y”~ ._ _.+=’z_&~% . . ...
Chord Iine-.l ._. ---
-a3~
0“ z -14 -M -/2 -12 ao, d;g -.----- - ------- - 8 -16 8.
—.- -to —-- —— -
4: -
——- ;: P 0 L@er surface P 0 @per surface A Lower ‘“ A Lower “ -6 -8 -6 -6 \ i -4 :4 -2 -2 c a -4----- +---- ----
e
I I .
l .->--
Chord line..
Chcrd line.. /--- -Q.
-c
.-6@;~.-.-===pz+z~ ----
...... , <q’ @--–- -=4 -It “ ‘i6 -i4 -i4 .
-i; -i!z .
@, ffeg —- ------- .
-/l -10 —-.
. . . . . . . .
——.
;: —— .
2$
P o @per surface P 0 i@per surface b ~ Ower It A Lower R -1 “8 \ -.5 -6 i \ -4 -4 i FIIIo%~ 6,-PrMTIM dlatrlbntton on tbo NAOA Z3C112 alrtoil with tbo dxad dot and 0.2M6cslothd tlsp St FIOUBB11.-Pmmura dlstrtbntlon on tho NAOA 98012alrfotlwith tbe @d dot mud0.!J6Mc clotted !kp U w tiOM ~@E of nttnok, fip dOd13Ct[O~ 10”, lowangh d l rook. Fllp dodwtlo~ 23”, ,, ,: i -18 -16 ‘/6 z o -14 -14 +2 +2 *, geg a,, deg —- —- .
-: -lo -lo ------- _ --- ..---- —— - —--
f$l
1$ o L@per surface P 0 L&er surf9ce P b Lower w A Lower *’ -8 -8 .
-6 ‘6 -4 -4
An/
// ,#--q ‘
‘.\
-2 -2- “\\:a%
/
“-=-i+
3/
P ~— ------- —..
4 0- .
*&----*----y& ~- ——
llf==’~b- -
-=== 1- ) .
-18
“i:\ /
-16 -16 -14 -14 .
-12 +2 C#O,o’fq —- -; -/0 0 -10 -------- -------- —-. ——.
i 1: P ‘P 0 @per surfoce 0 @per surface A Lower * A Lower II -8 -(5 -6 -6 -4 -4 #l -2 -2 ~, , ,U ---- + - ..
,. - . .
G .& . ...*...-
L
I
L
PIOtiE 10.-PrwuIra dktdhltb on tha NAOA ~M dtiO!] with the fIX~ slot and - Sbttd f@ mum 9.–Pmsnura distribution on tha NACA 28012 alrfoU with tha tlrcd nlotsad 0.’2WC dotted fip nt at VW1OIU nww of attnok. map deiIeoUon,OOO.
VMow anelw 0( attaok. Flap denmtton, 00”.
,, 92 REPORTNO. 73*NATIONM ADVXSORY COMMX!ITEll FOR AERONAUTICS The shapea of the presmm curves for the model with is reamnabIe to ass~e that the pressures on other flapswould be onIy slightly changed. It is to be remem- the slotted flap deflected (figs. 4 tQ 10) are generdy bered that the forem on the slat would change with very similar to those of the curvw for the slotted flap any alteration in shape of slat or slot.
deflected on a plain NACA 23012 airfoil (reference 7); A comparison of the pressures over tlm plain airfoil this similarity shows that the flaps have the same characteristic as to extent of peak pressure, occurrence with pressures over the slotted airfoil at the same angle ~f attack (fig. 11) and a comparison of the prcsnms I >ver the plain airfoil with slotted flap with the pres- — P/oil Okfoil &- 1.31 [reference 7) mre$ over the slotdml airfoil with slotkd flap at the ---- slotkcf airfoil cm-/,38 -4 \ wme angle of attack (fig. 12) show the following: The ‘.
\ plain and slotted combinations both carry about the P] wune load. The addition of the slot does not changa peak nom pressure h any extent. Tho center portion -2- ‘., \ ]f the slotted airfoil carries moro load and th slat :arries less load than a proportional section of plain ~irfofl. The load on the flap is slightly increased by o- the addition of a. slot.
The main effect of the tied slot on tlm plain airfoil with dotted flap is to increase tho angle of attack for .
FIOUM 11.-Compexkon 01 tbe PmSUI@ dhtrtbution on tho NACA 23012 8bfO~ the stall. The continuation of flow about tho airfoil with a fixed clot with that on a plaln NACA 2K112 ahfotl. apl~.
at high angles of attack accounti for the oxtrwnely of double peak pressures, and magnitude of peak nega- high vahms of P obtained.
tive pressures No chord-form diagrams were included in this report because of the simihwity of pressures on the slotted flap in this investigation to pressures on the slotted flap reported in reference 7 and because such diagrams can bo constructed from normal-forco FY&I airfdl &h sloifad flop diagrams.
c. -2.49 (refa-ence 7) The pressure curves for the fixed slat (&s. 3 to 10) ------ SkJtee;;lbil w% Shfkf f~ are similar in. general shapo to the curves shown in references 2 and 4, but the maximum peak negative -6 \ pressures are muoh higher on the fixed slat than they were on the Handloy Page typo of slat. The extremeIy p ‘\,
K
high negativo pressures (P= –18) at the now of theslat I i\ i might be fiery detrimental at relatively high &@ano speeds because of compressibility effecte. A careful \\ inspection of the prwsure curves will show that the \ location of the extremely high negative valuee of P is very critical. It is quite possible, therefore, that in -2 - the previous investigations of Handley Page slots the pressure orifices were so located that they inadvertently missed these high negative pressures. Diagrams show that the pressure vru-iation over the lower surface. of the slat is similar to the prewmre variation over the /- lowar surface of the main airfoil at the slot entry for the sIotted flap.
FmvR812.-0om_ c4 the prwsum dtetribution on tbn NACA =1~ difoll with a H dot and l OSSddc alottal dsp wltb thatons pWn NAOA ZKIIA tbfotl The preaaure diagrams for the center prtion of the wItb 0.25Mc dotted tip.~p derlectlw w q-lP’.
airfoil (figs. 3 h 10) show a similarity to the pressure AERODYNAMIC SE~ON CEARACTER1STIQ3 diagrams for a slotted flap.
The similarity of flow about the main portion of the A compariem of the section characteristi~ for the airfoil for several airfoil-flap arrangements (reference 8) combination (%. 13) with results reported in refer- indicates that the forces on the fied slat in combination ences 1 and 7 shows the following: Tho normal-force with any of the flaps would have approximately the coefbienta for the combination agree very well with same pressure curve as to magnitude of preaeuree and the force-test results of reference 1; the pitching- general shape. Because the addition of the bed slot moment coefficient for the arrangement &ted chow an had little effect on the pressures on the slotted flap, it increase over the ccticienta for the plain airfoil with PIUMSURE DISTR~IYTTON OVER NACA 23012 AIRFOIL WITH FIXED SLOT AND SLOTTED l?lL4P ---- , .-— ..- -2 0 .2 .4 .6 .8 10 A2 14 L6 I& 20 22 2.4 2.6 2.8 -.4 . .
h&maI-fMce cweffibienf of comh+mtibn, ~ ---- FLmrBE 13.-&etion chsmcf&sti~ of the NACA ‘ZKIM airfaiiwith tkdsed slot and O.Z&l& dotted clap.
mmom NO. 732-NATIONAL mvrsmy commmm mB mRONAUTICS Normd-fme coefficient of .canbInfftbn, c= mmm M.—aectkmokuacMWm clthe OJ660c tit onthe NACIA =12 atrfoiltith O,W alotfsd @ PRESSURE DISTRIBUTION OVER NACA 28012 AIRFOIL WtTH FIXED SLOT AND SLOTTED I?IAP 95 .
0 I 2 3 45 67 .“\ \ Scale of vecfors @osed m c=) ‘%--_---j -.== ------- -
22e\\a;6 “
--- -- —.
+-. — ~.
------
J
— /“ / ., f Fmum 15.–Veotmtelroprcsentatbn cJrmltentfmm ccdh?lent oftkeO.105.ksIat on the NACA ZlOIZ nkfotlwith the02606c dotted flu% ~POILT NO. 782—NATIONAL ADVtiQRY COMMIl”l’EE FOR AERONAUTICS Nod-force mefficieni of cmibinafim, C= Fmum lU.—&otkm oknctwlstlca of tbeO.ZMOc s!ottcd ftsP on tha NAOA 23012slrfoit with tha &d slot.
PRESSURE DIST=UTION OVEB NACA .23012 AIEFOIL WITH ~ SLOT AND SL0TT13D FLAP slotted flap (reference 7); and because the normal- The forces on the slat were smaUerthan the forces on force coefficients remain approximatdy the same on the same portion of a pkir.1airfQflat low angles!of attack both airfoils for a given fmgIe of attack, the center of but budt up ta very high values above the stalJof the _ pressure moves rearward.
No quantitative campmisort plain airfoil. These forces were much higher than of pitching-moment coeflkients with force-twt results previowdy pubIished Ioads on HandIey Page slats.
is made because the chord forces of flap and airfoiI The loads on the flap on the sIotted airfoiI were ap- have been negkcted in this report; however, the valuw proximately tie same as the loads on a flap on a plain of c. obtbed by the two methods show reasonable airfoil; therefore, any conventional ffap should show little chmge in load if a similar leading-edge slot were ._ agreement. The angle of attack for the EMI is slightly lower for the pressure-distribution tests, but no etlort added to the oombinat.ion.
was made to obtain absolute valuea because the same q~ent had been reported in reference I.
Figures 14 and 15 show the section characteristics of the dafi alone. The resultant-force coefEcient for the Lmc+mm MEMOEIAL Amomumcu hBOmTOIiY, slat tested is much higher than that reported for the NAmONAL ADVISORY COMMITTEE FOB AERONAUTICS, HandIey Page slat (references 2 and 4). The forces, LNGLEY FIELD, VA., Jdy W, 1941.
however, act in the same direction and from approxi- REFERENCES matdy the same point. The maximum resuhsmt force acts forward along a line that makes an angIe of ap- 1. Bamber, M. T.: Wind-TunneI ‘I%sta of Se~eraI Forms of proximately 47° with the chord line and intersects it at Fii Wig Slot in Combination with a Slotted FIap on an the 0.40 c. point, F~a 15 should be useful in the N. A. C. A. 23012 Airfoil. ‘1?.N. No. 702, NAG~ 1989.
design of sIat supports.
2. Jacolm, E@man N.: Prwwre Distrfbutfon - on a SIotted R. A. F. 31 AirfoiI in the Variable Density Wind TunneL A comparison of the section charaotezjst.ics of the T. N. NO. 308, NAC&1929.
flap aIone (&: 16) shows that the loads on the flap build up more slowIy than do the loads on tie mmbina- 8. Cauvain, William E.: Wiid-Tunnel Teats of a Clark Y Wiig with %laxw$dl” I.eadin&Edge ~OtS. T. N. No. 598, tion, except in the normal-force-coefficient range below NACA, 1937.
1 with flap deflections greater than 30°. A comparison 4. Ormerod, A.: Slotted R. A. F. 34 Bridal FfgMer.-Meamra- of the section characteristics of the flap alone on the ment of Forces on Slat in Flight. R. & M. No. 1477, slotted airfoil @g. 16) with the section characteristic British A. IL C., 1932.
of the flap alone on a plain airfoil (reference 7) shows 5. V%nzinger, Carl J., and Harris, Thomas L: Wind-Tunnel the flap loads and moments to be little affected by the Inwsatigation of an N. A. G. A. 23012 Airfoil with Various addition of the leading-dge slot. Inasmuch as the Arrangement of Slotted Flaps. Rep. No. 664, NACA, loads on the &p in combination with a slotted airfoiI 1939.
are approximately the same as the loads on the flap in 6. Pinkerton, Robert M.: The Variation with ReynoIds Number combination with a lain airfoil, no chord-force co- of Pressure Distribution over an AirfoiI Seution. Rep.
eflicient.s are given. $ he chord-force coeflicienta re- No. 613, NACA, 193S.
ported in reference 7 shouId be applicable.
7. Wenzinger, Cad J., and DeIano, James B.: Presmre Dis- tribution over an N. A. C. A 23012 Airfoil with a SIottgd CONCLUSIONS and a Plain Flap. Rep. No. 633, NACA, 193S.
The peak pressures at tie nose of the slat were very 8. Wenzinger, Cari J., and Ragallo, Francis M.: IMsurd of high in the range of angIe of attack where slots are Air-Load Data on Slats and FIaPs. T. N. No. 690, Usefd. NACA, 1939.
REPo~ NO. 732—NATION& ADTTf30RY CObfbfMTEE FOR AERONAmICS TABLE H.-ORIFICE LOCATIONS ON AIRl?fXL-SLOT- FLAP COMBINATION TESTED [Ori5ce locations on upper and lower wfaces ~ w~cnt aifloll ahord from Imding edge of airfoil] .—. .— -—.—-—- AlrbIl Ffxed .sht Blotted &p
I
W )rlflu )Ima TABLE I.-ORDINATES FOR AIRFOIL AND SLOTTED FLAP AND PATE OF FLAP NOSE [AU dimemionn h Pm’mnt of wtng ohord] BLOTTED FLAP NAOA .2’W2 AIWOIL L=mer -L a o ......
-z 0s L 23 Z 67 -!. B
I -% 21 2.5 a. 61 -L 71 -2.w b.o 4.91 -9.!M –z.u 7.5 &!m -% 61 -z 41 10 6.48 -% 92 ----- 7.19 -a 50 ... ... ; 7. bo –8.97 — -!216 7.00 4s l - mrraca only.
-440 E 7. M * upper .snrfam only.
% 7.14 ~~ # 0.41 6.47 -a. 07 ------ 4.30 -1. ‘as -&W -. m E .Kg -216 -L~a -.la .9a .18 Z la z L4dingage rsdhx 1J8 do of radius throngh r en Ofohord: O.sm.
00NTOUR OF SLOT PATH OF FLAP NOSE r
==F=l #
1“
naa -L M 7k m .07 o :A ael m.aa am k!!
?7. a2 3 &a a.4b
‘nal 965 ao !ada &w al. w %U 40 1.ab au e2m a64 50 .50 Lb3 W .M L&