NASA GA Fowler and Spoiler

8/3/2019 NASA GA Fowler and Spoiler

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INVESTIGATION FOWLER FLAP A N D SPOILER FOR

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We Puulson, Jr.Reseurch CenterVu. 23665

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N A L A E R O NA U T IC S A N D S PA CE A D M I N I S T R A T I O N W A S H I N G T O N , D. C. J U N E 1976


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TECH LIBRARY KAFB, NM

- ~~1. Report No. 2. Government Accession No. 3. Recipient's Catalog No.NASA TN D-8236

4. Title and Subtitle I June 1976WIND-TUNNEL INVESTIGATION O F A FOWLER FL AP AND 6. Performing Organization CodeSPOILER FOR AN ADVANCED GENERAL AVIATION WING I~

7. Author(s) 8. Performing Organization Report No .John W. Paulson, J r . L-1073610. Work Unit No.

9. Performing Organization Name and Address 505-10-11 -03NASA Langley Research Center 11. Contract or Grant No.Hampton, Va. 23665

13. Type of Report and Period Covered12. Sponsoring Agency Name and Address Technical Note

National Aeronautics and Space Administration 14. Sponsoring Agency CodeWashington, D.C. 20546

16. AbstractAn investigation h as been conducted in the Langley Re sea rch Cent er V/STOL tunnel to

deter mine the ef fects of adding a Fowler flap and spoiler to an advanced general aviation wing.The wing was te ste d without fuselage o r empennage and was fitte d with approximately th ree quarte r-span Fowler flaps and half -span spoi lers. The spoilers were hinged at the 70-percentchord point and vented when the .flaps were deflected. Static longitudinal and lat era l aer ody namic data wer e obtained ove r an angle-of-attack range of -80 to 220 fo r various flap deflections and positions, spoil er geometrie s, and vent-lip geomet ries.

Lateral characteristics indicate that the spoilers are generally adequate for lateral control. However, the spoilers do have a reg ion of low effe cti ven ess when deflected less than 100o r 15O, espec iall y when the flap s are deflected 30 or 40. In general, t he spoile r effectivenes s inc rea ses with incre asing angle of attack, in cre ase s with incre asi ng flap deflections, andi s influenced by vent-lip geometry. In addition, the data show that so me two-dimensionaleffects on spoiler effectiveness are reduced in the three-dimensional case. Results also indicate the expected significant i ncr eas e in lift coefficient as the Fowler flaps are deflected; whenthe flap was fully deflected, the maximum wing lift coefficient was increased about 96 percent.

17. Key-Words (Suggested by Authoris)) 1 18. Distribution StatementLateral control Unclassified - UnlimitedSpoiler sFowler flapsGeneral aviation Subject Category 08

-. ~For Sale by the Na tion al Technical Info rma tion Service, Springfie ld, Virginia 22161


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WIND-TUNNEL INVESTIGATION OF A FOWLER F L A P AND SPOILERFOR A N ADVANCED GENERAL AVIATION WING

Joh n W. Pauls on, J r .Langley Research Center

SUMMARY

An investigation has been conducted in the Langley Res ea rc h Cen ter V/STOL tunnelto d etermin e the eff ec ts of adding a Fowler flap and spoiler t o an advanced gener al aviation wing. The wing was t est ed without fuselage o r empennage and was fitted with approximately three -quar ter -span Fowler flaps and half -span spo ilers. The spo iler s werehinged a t the 70-percent chord point and vented when the fla ps we r e deflected. Staticlongitudinal and late ral aerodynamic data we re obtained over an angle-of-attack rangeof - 8 O to 2 2 O for var ious flap deflections and positions, sp oiler ge ometrie s, and vent-lipgeometries.

Lateral cha ract eris t ics indicate that the spoilers a r e general ly adequate for later al control . However, the spo iler s do have a reg ion of low effe ctiv ene ss when deflec tedless than loo o r 1 5 O , especially when the flaps a r e deflected 30' o r 400. In general , thespoiler effect iveness incre ase s with increasing angle of at tack, incre ase s with increas ing flap deflections, and is influenced by vent-lip geome try. In addition, the d ata showthat som e two-dimensional effects on spoile r effectiveness ar e reduced in the three -dimensional case. Results a lso indicate the expected significant inc rea se in lift coefficient as the Fowler flaps are deflected; when the flap was fully deflected, the maximumwing lift coefficient was incr eas ed about 96 percent.

INTRODUCTION

The development of new, thick, high-lift air fo il secti ons ha s had a profound effect onthe gen eral aviation community because these section s offer the possibility of improvedperfor mance on se ve ra l new light air cr af t designs. These airfoils provide higher maximum lift coefficients than the conventional 64-Series air foil s used on many gen era l aviation airc raf t. This i ncr eas e in maximum lift coefficient allows the use of a smal ler ,mo re highly loade d wing with less wetted area. These developments can increase cruiseperfo rmanc e and improve ride quality. The increa sed thickness of thes e airfoils alsoprovides t he opportunity fo r wing s tru ctu ral weight savings.


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With an appr opr iate high-lift device suc h as a full-span Fowler flap, further reductions in wing area may be achieved, and the desi rab le low landing spe eds of typic al lightair cra ft can be maintained. Full-span flaps, however, gener ally preclude the us e of conventional ailerons, and an alter nate method of lateral control is needed. One suc h methodwould us e partial span spoi lers (also known as slot-lip ailerons) . Several airplanes whichus e Fowler fla ps with the advanced airfoils are alre ady in either the design stage or ea r l yflight-t est s tag e of development. (See ref. 1.) Some of th ese a irp lan es use the 17

' percent- thick General-Aviation (Whitcomb)-1 ai rfoi l usual ly r efe rre d to as the GA(W)-1.(See refs. 2 and 3 . ) One part icula r ai rcr aft which us es this airfoil i s the Advanced Technology light twin (ATLIT). (See ref. 1.) This airc raft u se s nearly ful l-span Fowler flapsfo r low-speed perfor mance and half -span s poile rs f or lateral control. Thes e spo ile rsare vented when the flaps are extended and unvented when the flaps are re t racted.

Before the original flight of the ATLIT, th er e w a s concern about the effectivenessof the sp oi le rs at sma ll deflections when the flaps wer e deflected 40 because of two-dimensional data (refs. 4 and 5). The data of ref ere nce 4 indicated that the sp oiler s hada region of ve ry low effect iven ess when deflect ed less than l o o o r 15O. In addition, th er ewas control reversal under certain conditions. If a sm all left spo iler deflection was given- cin an effort t o produce a negative (left wing down) rolling moment, the res ult w as a ctuallya positive (right wing down) rolling moment. This investigation w a s undertaken to d eter -mine to what extent, if any, thes e two-dimensional e ffects were ppesent on a three-

% .dimens ional wing. .tThe investigation w a s conducted in the Langley V/STOL tunnel by using a rectangu

lar wing with Fowler flap and spoilers. Static fo rc es and moments were obtained for thewing with various flap deflections and positions, spoi ler deflections, spoiler cr os s -sectiongeometries , and vent-lip geome tries.

SYMBOLS

The data are pres ente d in the stability-axis syst em shown in figu re 1. The modelmoment center was 25 pe rce nt of the wing chord. A l l measurements and calculations .were made in U.S. Cus toma ry Units; however, all values contained in this study ar e givenin both SI and U.S. Cust om ary Units. (See ref. 6.)

b wing span (without subscr ipt ), span of flap, o r vented spo iler (with sub scri pt),m (ft)

DragCD dra g coefficient, q,s

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CL lift coefficient, -if tqcosCl rol ling -moment coefficient,

Cm pitching -moment coefficient,

Cn yawing-moment coefficient,

Rolling momentq,Sb

Pitching momentq,se

Yawing momentq,Sb

CY side -for ce coefficient, Side for ce%asC wing chord, m ( f t )-C mean aerodyna mic chord, m (ft)

P roll rate , rad/s ec

pb/2V, wing-tip helix angle, rad (see appendix)g, f ree - s t r eam dynamic press ure , Pa (lbf/ft2 )R radius, percent of wing chord

S wing area, m 2 (ft2)v, fre e-s tr eam velocity, m/s ec (f t /sec)X longitudinal dimension (see fig. 1)

X/C longitudinal distance fr om wing leading edge with res pec t to mean aerodynamicchord

Y lateral dimension (see fig. 1)

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z

CY

6 Subscripts : f max S

vertical dimension (see fig. 1) angle of attack of model reference line, positive nose up (fig. l ) , deg deflection of flap or spoiler (fig. 3), deg

flap maximum spoi ler

APPARATUS AND PROCEDURES

This investiga tion was conducted in the Langley V/STOL tunnel in suppo rt of theATLIT air cra ft pr og ra m to determine the gen eral char acte risti cs of an ATLIT-typeFowler flap and spoiler lateral-contr ol s ystem. An existing aspect-ratio-8.98 rectangu larwing with the GA(W) -1 airfoil sec tion was modified to acce pt the Fowler flap and spoileras shown in fig ur es 2 and 3(a). The wind-tunnel model was not intended t o re pre se nt theATLIT tapered wing exactly but rat her to be a gen eral repr ese ntati on of the ATLIT Fowlerflap and spoiler system. Tables I and 11 give the coordina tes of the GA(W)-1 wing se ctionand flap section, respectiv ely. The wing had a sp an of 4.01 m (13.16 ft) , a chord of 0.45 m(1.46 f t ) , and an area of 1.79 m2 (19.31 f t 2 ) . When the f laps w er e fully deflected, the wingarea was in cre ased by 17 per cent t o 2.10 m 2 (22.59 ft2) . The wing root was a t an incidence of 20 and the wing was line arly twis ted to a tip incidence of Oo. For this investigation, the mod el re fer en ce line was defined to be the wing-tip cho rd line.

The Fow ler fla ps wer e made in four se ctio ns on eac h wing panel (fig. 2) but werealways deflected as a unit. Each flap section was mounted on bra ck ets to allow deflectionsof 00, 100, 200, 300, and 400. Table Ill shows a comple te lis ting of flap deflection andposition as well as the spoile r and vent-lip geome tries for this investigation. Figure 3(b)shows the flap overlap and gap dimensions corresponding to the v ario us flap deflectionsand positions. The flap chord w a s 30 per cent of the wing chord and the flap span ra tiobf/b/2 was 0.764.

The spo iler s we re made in four s ections fo r the left wing panel only. (See fig. 2.)In or de r to simulate the ATLIT spo iler-span wing-span ratio, only the thr ee outboardsections wer e deflected during the investigation; the inboard s ection (spoiler section a)

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remained sealed at all t imes. The three operative spoiler sections (b, cyand d) had aspan ratio bs/b/2 of 0.572 and were hinged at x/e = 0.70. (See figs . 2 and 3(a).) Thehinge line was offset 0.015e forw ar d of the leading edge of the sp oil er so that the trailingedge of the spo ile rs w a s located at x/e = 0.80 when 6s = 00. This offset hinge lineallowed a gap to open between the wing upper sur face and the sp oil er leading edge as thespoi ler w a s deflected. (See fig. 4.) Each spoiler section w a s remova ble and could be re plac ed with one of thr ee sp oil er cro ss -s ect ion geo metr ies ( also shown in fig. 4). The ventlip (the downstr eam lip of the spo il er vent) as w e l l as the spoiler geometry w a s variedduring the tes t as shown in figure 5. The model installation in the V/STOL tunnel isshown in figu res 6 and 7.

Most of the inves tigation ti me was concen trated en the c as es with 400 flap deflection.At 400 flap deflection, t he control effec tiveness problem areas which were indicated in thetwo-dimensional data of r efe ren ce 4 we re examined over a spoiler-deflection range of 00to 450 fo r different combinations of spo ile r c ro ss -section g eome try an d vent -lip geometr y.Lower flap deflections were tested to obtain longitudinal and lateral data, but these testswere run by using only the triangular backed spoiler (spoiler B) and the lar ge ra dius ventlip. Angle of atta ck ranged fr om -8O to wing st al l.

Most of the da ta wer e obtained at a dynamic pre ss ur e of 1.44 kPa (30 lbf/ft2); however , because of hard ware c ons train ts, so me data were obtained at a dynamic pr ess ureof 0.48 kPa (10 lbf/ft2). Whenever the dynamic pr es su re was lowered to 0.48 kPa (10lbf/ft2), a single pair of ru ns w as m ade with the identical configuration at both the highand low dynamic pr es su re s to establish Reynolds number effects. The Reynolds numberscorresponding to these dynamic pr es su re s are 1.49 Y l o 6 and 0.85 X 106, respectively. Itshould be noted that at the lowest dynamic pr es su re , the Reynolds number is s ubc ritic alover a la rg e portion of the wing chord.

Transi t ion w a s fixed at 2.24 cm (0.88 in.) downstream fr o m the leading edge fo r theupper sur face and 4.32 cm (1.70 in.) on the lower surf ace ( ref . 7) . Data were correctedfo r tunnel wall effects of r ef ere nce 8; no other cor rec tions wer e applied.

PRESENTATION OF RESULTSThe data of th is investigation have been red uced to coefficient for m and are p r e

sent ed in the following figu res:Figure

Effects of flap position and deflection on spo ile r B ch ara cte ris tic s . . . . . . . . 8Effects of vent-lip ge omet ry on sp oil er B character i s t ics . . . . . . . . . . . . . 9 and 10

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FigureEffe cts of vent -lip geo met ry on spo ile r C charac te r i s t i cs . . . . . . . . . . . . . 1Spoiler A character i s t ics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1Effe cts of s eque ntial deflection of sp oil er B eleme nts b, c, and d . . . . . . . . . 1Effects of dynamic pr es su re . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.Effects of flap position s and deflections on wing longitudinal ch ar ac ter is tic s . . . 1Rolling mom ent s gene ra ted by deflection of sp oi le rs B, C, and A . . . . . . . . . 6 to 1

DISCUSSION

The effects of spo iler deflection, with vario us flap positions, cro ss- sec tion ge ometri es , and vent -lip geome tries, on the longitudinal and lateral ch ar ac ter is tic s of the wingare presented in figure s 8 to 12. It may be seen fro m these data (part icularly CL andC2 plotted against a ) that the vented spoile r effectivenes s is ve ry low when deflectedles s than 100 to 150. In figure 13, the sequential spo iler deflections (sequences 1 and 2)confirm the trends of the previous data; the spoiler effectiveness remains low until thespoiler elements are defle cted 150. The data of fi gu re s 8 to 13 we re used to constructthe lift, dra g, and pitching-moment cur ves of figure 15 with 6 , = 0 and the rolling-moment curves of figures 16 to 18.

The effects of Reynolds number a r e pr es en ted in fig ure 14. The effects on the longitudinal data wer e s ma ll with the typical in cr ea se in C L , ~ ~t the higher Reynoldsnumber. The effects on the lateral data were somewhat inconsistent but gen erally notlarge.

Longitudinal CharacteristicsTh e data of fig ur e 15(a) show the longitudinal char ac ter ist ic s of the wing at flap

defle ctions of 00, 100, 30, and 400. The basi c wing has a des ign lift coeffic ient of 0.4at a = 0.5' and a maximum lift coefficient of 1.32 at CY = 16.7O. At the maximumflap deflection (6f = 40), t he maxim um l i f t coefficient is incr eas ed 96 perce nt to 2.59 ata = 12O. Figure 15(b) shows the ef fect of moving the flap at 6f = 40 from x/E = 1.00to 0.96. Both lift and dr ag are reduced as the flap lose s s ome effe ctiveness when movedbeneath the tra ilin g edge of the wing. The dr ag cur ve s show the typical high dr ag levelsasso ciated with the la rg e flap deflections. In addition to the high lift and drag, the flapsproduce large nose-down pitching moments which must be trimmed for aircraftapplications.

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Lateral Character i s t icsThe rolling moments ge nerat ed when spoi ler B was deflected at various flap settings

are given in fig ure 16. For the c lean wing configuration (6f = 00, fig. 16(a)), the rolling -moment variation with spoiler deflection is reasonably linear, but somewhat less effectivethan that of conventional ail er on s (ref. 9). A t the maximum spoiler deflection of 45O, thewing-tip helix angle pb/2V, i s 0.044; thi s helix angle is low accor ding to ref ere nce 10which sta tes that 0.07 is an acceptable level. (The method used to calculate pb/2V, isdis cus sed in the appendix.) However, a mo re r eali stic maximum deflection might be 60or 700; such a deflection would prob ably inc rea se pb/2V, t o a mor e acceptable level.Thi s low effectiveness is apparent only with 6f = 00; with the fla ps deflected, pb/2V,is significantly higher.

When the f lap s are deflected 100 at x / E = 0.917 (fig. 16(b)), the rolling-momentvariation with spoil er deflection becom es mo re nonlinear and develops three ra the r di stinct region s of effecti venes s. A regio n of low sp oil er effectiv ene ss below 6s = 150becomes apparent. A region of inc rea sin g effe ctiven ess between 6s = 150 and 200 fol lows. Finally, the region above 6, = 200 shows fa irl y high lev els of spo iler effectivenes s. Although thes e regio ns are not pronounced at'the l o o flap deflection, they do indicate the trend s which become rath er larg e at the 300 and 400 flap d eflections.

Fig ure 16(b) shows that the rolling moments become mor e sensitive to angle ofattack as the flap i s deflected. The clean wing had a variation in maximum Cz from0.045 to 0.050 at angles of a tt ac k of -40 to 80 , and the wing with 6f = 100 had a variationin maximum Cz from 0.056 to 0.073 at angles of attack fro m -40 to 80 . The wing with6f = 100 and 6s = 450 had a pb/2V, ranging from 0.046 to 0.059 cor res pon ding to thehigher rolling moments. The highe r pb/2V, i s indicative of the inc rea sed controlpower available with the flaps deflected.

When the flaps a r e deflected 300 at x / E = 0.960 (fig. 16(c )), the rolling-momentvariation with spo iler deflection beco mes ve ry nonlinear and is seg mented into three v erydistinct regions. Thes e regions corre spond to the regions of the data at 6f = 100 discuss ed ea rli er , but ar e much mor e pronounced. The region of low spoi ler effectivenessbelow 6f = 100 which was of conc ern in the two-dimensional data i s ve ry ap parent. A sin the l o o flap-deflection case, the rolling moments are sen siti ve to angle of attack withmaximum Cz var ying fr om 0.099 to 0.122 at angl es of at tack of -4O and 8O. The pb/2V,corresponding to each of the se r olling moments w a s 0.083 to 0.099. Here again theincr eas ed control power available with the flaps deflected w a s shown. Although the se dataare quite nonlinear, they are smooth, without re ve rs als in slope, and appear to be adequatefor lateral control .

When the flaps are deflected 40 a t x / E = 1.00 (fig. 16(d)), the rolling-m omen tvariation with spoi ler deflection st ill indicates thr ee regions of spo iler effectiveness;

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however, the data in the low effectiveness region (tjS = 150) show large re ve rs al s in slopThis change in spo iler effec tiveness i s probably caus ed by intermittent flow separatio ndownstrea m of the vent. Above 6s = 150, however, the s poi ler effec tiveness no longershows slope rev ers als . The rol l ing moments are st il l sen siti ve to angle of attack, andthe pb/2V, rang ing fr om 0.089 to 0.123 sho ws a furthe r increa se in control power avaable at 6f = 400. It should be noted that thi s configuration did have the la rg e r adius venlip and that some of the slope r ev er sa ls prese nt at 6 s 5 15O wer e c orrect ed when diffeent vent-lip geome tries we re used.

Effect of Vent-Lip Ge ometry and Fl ap Effect ivenes sThe two-dimensional mod els of r efe ren ce 4 used vent-lip geo met ries which we re

sim ila r to both the blunt-lip and the sh arp-lip geo met ries us ed in the three-dimensionalmodels. It was origin ally thought that the regions of low sp oi ler effecti venes s and contr ore ve rs al s (regions of concern in ref. 4 ) we re the res ult of flow separ atio n downstream ofthe sharp-edged vent l ips. Control re ve rs al s wer e defined as a change in sign of the roling moment. (A left spo iler up contr ol input to give a nega tive ( left wing down) rolli ngmoment would actually produc e a positi ve (r ight wing down) rolling moment.) The twoadditional radius vent lips we re intended to reduce these pr oblem s. A s figure 17 shows,the rolling-moment data fo r the larg e and sm al l rad ius vent lips and flaps deflected 400do not show control r eve rsa ls, and the data for s ha rp and blunt vent lips and flaps deflect400 show only very slight control reversals. The two-dimensional control re ve rs al s evident in reference 4 are either eliminated or great ly reduced in the three-dimensionalmodel. However, the re was in al l cases a regio n of low spoi ler e ffec tivene ss below6 s = 100 to 150. A s shown previ ously in figur e 16(d), the rolling-mom ent data fo r thelarg e radiu s vent lip had large re ve rs al s in slope below 6 s = 150. However, none of theother vent-lip geometries exhibi ted such r ev er sa ls at ei the r flap locat ion x / E = 0.96 or1.00. In general, the spoiler effec tiveness incr eas ed with inc reasin g angle of attack bothin the lower effectiveness region and at the higher sp oile r deflections fo r all vent-lipgeome tries. Also, the spoiler eff ectiveness is higher with the blunt vent lip and with theflap located at x/C = 1.00. Moving the flap fr om x/E = 0.96 to 1.00 shows the sam etrend as that shown in figure 16; the sp oiler ef fectiveness inc re as es with inc reasin g flapeffectiveness.

Some data wer e obtained using other spo iler g eom etr ies on this wing. Spoiler Cwas s imi la r to the spoiler s used on a currently operat ional high performance general aviation aircraft. The third spoiler studied, spoiler A, was the T-type. The data for thesespo iler s with flap s deflected 400 are pre sen ted in fig ure s 18 and 19 and show the sa megener al char act eris tics of the data fo r spoiler B.

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S U M M A R Y OF RESULTSAn investigation has been conducted to de ter min e the effe cts of adding a full-span

Fowler flap and half -span spo iler t o an advanced gen eral aviation wing. The resul ts haveshown:

1. In general, the thr ee -dimensional data conc urre d with two-dimensional d ata of thereferen ces. The regions of decr ease d spoi ler effectiveness are l imited to spo iler deflections less than 100 o 1 5 0 and are most prominent at the highest flap deflections. Howeve r, the genera l effect of the three-d imensiona l model was to redu ce many of the character ist ics meas ured with the two-dimensional model.

2. The spoilers generally show acceptable lateral-control characteristics except forsome regions of low eff ecti vene ss at sma ll spoiler deflections.

3. The spoiler effectiveness was in crea sed when the flap deflection was increased.

4. The spoiler effectiveness w a s in cr ea se d when the angle of atta ck w a s increasedand the flaps w ere deflected.5. The spoiler effectiveness w a s affected by vent-lip geometry, and the blunt vent

lip gave the highest rolling moment.6. The Fowler flaps, as expected, significantly incre ased maximum lift coefficient;

the maximum lift coefficient w a s increased 96 percent for the maximum flap deflection.Langley Res earch Center National Aeronautics and Space Administration Hampton, V a . 23665 May4, 1976

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- -

APPENDIX

COMPUTATION OF WING-TIP HELIX ANGLE

The computation of t he wing-tip helix angle fr om st ead y-s tate lateral data dependson the ability t o determi ne the roll-damping derivative Clp. Refer ence 10 gives an equation fo r the wing-tip helix angle

where

1 6 change in rolling moment pe r degre e of spo iler deflection

6a spo iler deflection in deg ree s

ra tio of sp oil er chor d to wing chord

K corre ction to spoile r effectiveness because of large. deflections

All these t e r m s actual ly reduce to the rol l ing moment meas ured on the model with a lateral control deflected. The roll-damping derivative CZP may be est imated from ref er ence 11 which uses a vorte x-latti ce type of the ore tica l pred iction method, o r Clp maybe est imated from the ch art s in reference 10. F or this rep ort, the method of refe renc e 1was used. The ref ore , pb/2V, may be writte n as

Pb - (C1)measured2vm (CZP)calculated

10

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REFERENCES

1. Crane, Harold L.; McGhee, Robert J.; and Kohlman, David L.: Applicat ions ofAdvanced Aerodynamic Technology to Light Aircr aft. [P re pr in t] 730318, SOC.Automot. Eng., Apr. 1973.

2. McGhee, Robert J.; and Beasley, William D.: Low-Speed Aerodynamic Characteristics of a 17.-Percent-Thick Airfoil Section Designed for Gen era l Aviation Applications. NASA TN D-7428, 1973.

3. Wentz, W. H., Jr.; an d Seetharam, H. C.: Development of a Fowler Flap System f o r aHigh Per fo rm an ce Gener al Aviation Airfoil. NASA CR-2443, 1974.

4. Wentz, W. H., Jr . : Effec tiveness of Spo ile rs on the GA(W)-1 Airfoil With a High Performance Fowler Flap. NASA CR-2538, 1975.

5. Wenzinger, C ar l J.; and Rogallo, Fr an ci s M.: Wind-Tunnel Investiga tion of Spoi ler,Deflector, an d Slot Lateral-Contro l Devices on Wings With Full-Span Split andSlotted Fla ps . NACA Rep. 706, 1941.

6. Mechtly, E. A.: Th e Internat ional System of Units - Physical Constants and Conversion F ac to rs (Second Revision). NASA SP-7012, '1973.

7. Braslow, Albert L.; and Knox, Eugene C.: Simplified Method fo r De termination ofCr it ic al Height of Distributed Roughness Particles fo r Boundary-Layer Transitionat Mach Numbers From 0 to 5. NACA TN 4363, 1958.

8. Gillis, Cl are nce L.; Polhamus, Edward C.; and Gray , Jos eph L. , Jr.: Char t s fo rDetermining Jet-Boundary Cor rec tio ns for Complete Models in 7- by 10-FootClosed Rectangu lar Wind Tunnels. NACA WRL-123, 1945. (F or me rl y NACAARR L5G31.)

9. Paulson, John W., Jr.: Wind-Tunnel Test of a Conventional Flap and Aileron anda Fowler Flap a nd Slot-Lip Aileron for an Advanced G ener al Aviation Wing.Paper 750501, SOC.Automot. Eng., Apr. 1975.

10. Perkins, Courtland D.; an d Hage, Robert E.: Airplane Per for man ce Stability andControl. John Wiley & Sons, Inc., c.1949.

11. Tulinius, J.; Cl ev er , W.; Niemann, A.; Dunn, K.; and Gaither, B.: Theoretical Prediction of Airplane Stability Derivatives at Subcritical Speeds. NASA CR-132681,[19731.

11

II 11111111 11111.1111111 11111111 . 1 1 1 . 1 1 1 ~ . 1 1 1 1 1 1 1 II I 111 I 111111I 1 1 1 1 1 1 1 1 1 1 1 1 ~ ~ I ~ 1 1 1 1I II


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TABLE I. - GENERAL -AVIATION (WHITCOMB)-1AIRFOIL COORDINATES

Upper surface Lower surface

0.00000 .00200 .00500 .01250 .02500 .03750 .05000 .07500 .10000 .12500 .15000 .17500 .20000 .25000 .30000 .35000 .40000 .45000 .50000 .55000 .57500 .60000 .62500 .65000 .67500 .70000 .72 500 .75000 .7 7 500 .80000 .82500 .85000 .87500 .90000 .92 500 .95000 .97500

1.00000

0.00000 .01300 .02040 .03070 .04170 .04965 .05589 .06551 .07300 .07900 .08400 .08840 .09200 .09770 .lo160 .lo400 . lo491 . lo445 .lo258 .09910 .09668 .09371 .09006 .08599 .08136 .07634 .07092 .06513 .05907 .05286 .04646 .03988 .033 15 .02639 .01961 .01287 .00609

-.00070

0.00000 .00200 .00500 .01250 .02500 .03750 .05000 .07500 .10000 .12500 .15000 .17500 .20000 .25000 .30000 .35000 .40000 .45000 .50000 .55000 .57500 .60000 .62500 .65000 .67500 .70000 .72500 .75000 .77 500 .80000 .82500 .85000 .87 500 .90000 .92500 .95000 .97 500

1.00000

0.00000 -.00930 -.01380 -.02050 -.02690 -.03190 -.03580 -.04210 -.04700 -.05100 -.05430 -.05700 -.05930 -.06270 -.06450 -.06 520 -.06490 -.06350 -.06100 -.05700 -.05400 -.05080 -.04690 -.04280 -.03840 -.03400 -.02940 -.024 90 -.02040 -.01600 -.01200 -.00860 -.00580 -.00360 -.00250 -.00260 -.00400 -.00800

12


15/81

TABLE 11.- THIRTY PERCE NT c FOWLERF L A P COORDINATES

[Leading-edge radius = O.O122c]-~

Upper surfaceXf /"0.000 -0.01920

.025 .00250

.050 .01100

.075 .01630. l o o .01900

.125 .01950

.150 .01820.175 .01670

.200 .01330

.225 .00950

.2 50 .00530

.275 .00100

.300 -.00435

Lower surfac e*f /"-

0.000.025.050.07 5. l o o.125.150.175.200.225.250.275.300

-0.01920-.02940-.02490-.02040-.01600-.01200-.00860-.00580-.00360-.00250-.00260-.00400-.00800

13


16/81

TABLE III. - CONFIGURATIONS INVESTIGATED_.

-Spoerery Vent -lip geometry Fla p deflection and position, 6f/x/ETriangular back, spoiler B

Triangular back, spoiler Bsequential deflection)

Contoured back, spoiler C

(Ttypebaclt,spoiler A

14

- ..Blunt 00/0.713, 200/0.96, 400/0.96, 400/1.00

Small radius 400/0.96Large radius 100/0.917, 300/0.96,

Sharp 400/1.00Large radius .400/1.00

Small radius 40/0.96Large radius 400/0.96

Sharp 400/1 .00Large radius 400/0.96

. .. ---.. - - . . .


17/81

Figure 1.- Stability-axis sy ste m used in data presentation.

2

Figure 1.- Stability-axis sy ste m used in data presentation.

15


18/81

d C aI I 1

I I III I II I I

0.447(1.467

I

Flap brackets0.403 m (nested)

1.534

4.01 mSpoiler (left panel only)

u.441 mb / a --r-- r--1 (1.467 ft ) d I C I b I 1 r - -I - r--;:I II II II II r - - rI II I I I I I II -r I II Iim (Y:: ;;-l - I 0.403 m . -. Flap bracketsL .534 m (1.257 ft)(5.03 f t ) (1.321 ft) Fowler flap (nested)

I

Figure 2 . - Plan view of wing.


19/81

X/ C = 0.7 x/c = 0.8 x/c = 1.0x/ c = 0

I Spoiler -\j 1,

(a) GA(W )-1 airfoil with Fowler flap and spoiler.Figure 3. - Flap deflections and positions.


20/81

--v e r l a pGap

.Over lap, Gap,p e r c e n t C p e r c e n t C

0" 30.0 010* 9.6 3.120 5.3 2.630 5.3 3.640 5.3 3.640 :c 1.3 2.5

" A T L I T c o n f i g u r a t i o n s(b) Fowler-flap overlap and gap dimensions.

Figure 3. - Concluded.

18


21/81

x/c= 0.70-I- o-looc10.01 5c 0.003C

+t-t\ \ \ \ \ \ \ \ \ I \ \ \ \ I Spoiler A0.023~ T-type back

Hinge line 0.

t Spoiler BLeading-edge gap +. 23c. 4

- 0.017~Triangular backi

Hinge-,r/ Spoiler CWing 3 Contoured back

0.007~

Figure 4.- Cross -sect io n geometry of the thre e spoilers.

19


22/81

--

x/c = 0.80-L E luntR = 0 . 0 1 1 ~-1Small radius- I

-arge radiusI I

x /c = 0.839Figure 5.- Cross -sect io n geometry of the four vent l ips.

20


23/81

,

!

-~I Spoiler on l e f t Donet onlv ,1 . .~i 1f,

(a) Re ar view.

(b) Fro nt view. L-76-191 Figure 6.- Gen era l aviation wing in Langley V/STOL tunnel test section.

21


24/81

L -76 -1 9 2Figure 7. - Left wing tip of g enera l aviation wing.


25/81

--

I

- -

i I!7" -p.Jcm 1. - b , , de g. . . 0 0

I ! 0 2 . . . . . . . . . . . . . .I -04 A 6. . . j

I , b 8 10. . . . . . . -' O 15-1 - 0 20. . c D I 0 306eQ 0 45I- --- t*

-- +I . . . .I . . . . . . .I -:

" 1 - -~ I . I

!.iI I

j j ! I!ii . . .I ___ I ._ 1! ~, I J 4 8 - 12- - 16 20 24 a, de g

(a) Longitudinal characteristics; 6f = 00; x /E = 0.713; blunt vent lip.Figure 8.- Effects of flap posit ion and deflection on spoiler B c harac terist ics .

23


26/81

i

0.04 I 0ct -0.04

-0.08 . .I.. ... ..--I.. .. .... t -.---.,. .. ... 0 0I-0.12 I I .-,. .. 4 . I

- - I - - I - - - I i I 1 t0.02 I - - - 1.01 0c" 0 5-0.01- 0.02

0.02. . . .0.01

0-0.01-0.02 . . .. ........ 1 ...... t .. - .

-1l l .,-a -4 0a, de g

(b) Lateral character i s t ics; 6f = OO; x / E = 0 .713; blunt vent lip.Figure 8 . - Continued.

24


27/81

... . . .

4 a 12 16 20 24

(c) Longitudinal chara cter isti cs; 6f= 100; x/E = 0.917; lar ge ra dius vent lip.Figure 8. - Continued.

2 5


28/81

-- -

- -

0.04 . . . ..I. . .I0 *

t -0.04 T0.08 - ....- . . . .-0.12 . . . _ I .

I- - I -I0.02 . . . . . . . .0.01

c n O-0.01- 0.02 I

0.02..-.I..

~

I0.010

-0.01 !i I; - , .. . ; . ... .i i - .. +-0.02 . . t

~ i !II. . . . . . . . . . . . . . . . . i -.1. . . . . . . . . .-8 -4 0 8a. deg

(d) Lateral charac te r i s t i cs ; 6f = 100; x / E = 0.917; lar ge rad ius vent l ip.Figure 8. - Continued.

26


29/81

I II I II. . i... cm 8 , , de g

0 0I 0 2. J-. . 0 4Ij n 6 . i 0 8 i I3 10 n 15 i

i 0 20 c D 30+ 45. I . .-I- ...I...c L

- .I1i ... . . @ !. ..-- 1 . -I II- I '' r 'II ! ii----I' I-0.4.. . ... .-8 4 8a, deg

(e) Longitudinal cha rac ter istic s; 6f = 200; x/E = 0.96; blunt vent lip.Figure 8. - Continued.

27


30/81

0.010

c2 -0.04-0.a-0.1i

0.020.01

C" O -0.01-0.02

0.020.01

O -0.01-0.02

-8 -4 4 a 12 16 20a , deg

(f) Lateral character i s t ics; 6f = 20; x / E = 0.96; blunt vent lip.Figure 8. - Continued.

6,, de g0 00 20 4 A 6 0 8n i on 150 200 30

_ __ _

24

28


31/81

1

0 I I I I ~ .

-. . t

.

II

- 1I - i iI

iI -8 -4 4 a. deg

(g) Longitudinal characteristics; 6f = 300; x /E = 0.96; large radius vent lip.Figure 8. - Continued.

29


32/81

6,, de g- 0 0

0 20 4A 60 8Ls i o0 150 200 30

9- 0 45

a, deg(h) Lateral character i s tics; 6f = 300; x/C = 0.96; large radius vent lip.

Figure 8. - Continued.

30


33/81

a, de g(i) Longitudinal cha rac teri stic s; 6f = 400; x / E = 0.96; blunt vent lip.


3 1


34/81

--.......... .. r. . - . . . .ki#. . . -

CI -0.04 6,, deg-..- .... 0 0

0 2......-. 0 4A 6-0.12 ! .... 1 jI...... ..... ...... L . . . . . . - ' ~b 8I ~

: 010

. . . ..- - -1... .......1 t i. . . - . . . . . . . . - . ............i................ . . . . . . . . . . .!. . . . . . . . . . . .!1

............I ), I .4 8 12 i 6 ' i

a, deg(j)Lateral character i s t ics; 6f = 400; x /E = 0.96; blunt vent lip.


32


35/81

1.2

.~ .

0 . *0.4 1 t;lB I 0 00 2-0.60.8

. . . . . I - .iI '- 0 4n 60 8n i o0.6 - .... . .... . . .. - n 15

I I-0.2 1 . cm

i 0 20c D 0.4 0 30

0.2 m %-b= 0 45I . ..I

2.81 . . . .. !~

Ij. .c L

-S6i -. . .$ I!I...

Ii - - - Ii-0.41. 1-8 -4 4 a. de g(a) Longitudinal characteristics; small radius vent lip.

Figure 9.- Effects of vent-lip geome try on spoiler B cha ra cte ris tic s with 6f = 400at x / E = 0.96.

3 3

I


36/81

0.010

cr -0.01-0.08-0.1i

0.020.01

cn 0- 0.01- 0.02

0.020.010

- 0.01-0.02

, de g0,24

.I. . 1. . -1. . ..... ..I

II

. . I .-8 -4

(b) Lateral ch aracteris t ics; s ma ll radius vent lip.Figure 9. - Continued.

34


37/81

--

...

.....

. - . .. -.cm iS ' de gd+-c 3 3 03 2.... .... > 41 6..... . .. 1 81 1 0-. 3 154 4 ) 20% i 3045. . ..~.0.21 -0

....2.8 ' I I i i2.4 4 3.+-2.0 j. .. /5 .&e ....1.6

c L I. . . . .1.2~0.8 . . I

. . . . . . .... ....... 1 - - 1 . . j . - II0.4

0 i - - 1 %. . . . . . . . -I... .~ .... ...... T ... I... I i-0.4 8 16 20 24

a. deg(c) Longitudinal cha rac teri stic s; l ar ge r adiu s vent lip.


35


38/81

a, de g(d) Lateral character ist ics; l arge r adius vent l ip.


36


39/81

c m

c D

c L

........... __-..8 ... . ~ ..2.4 ... . ....-, I , ,

a, deg(a ) Longitudinal characteristics; blunt vent lip.

Figure 10.- Effects of vent-lip geometry on spo iler B characte rist ics with 6f = 400at x/E = 1.00.

37


40/81

0.00

c -0.01z-0.01-0.1;

0. oi0.01

c n O- 0.01- 0.02

0.020.010

-0.01-0.02 1

I .... .... _..I. ...

1. . . . . . . . . . . . .I -.I . 1 --I I.......I. , . !

.I - . .-4 20 1 Ia, de g

(b) Lateral char acte rist ics; blunt vent lip.Figure 10. - Continued.

38


41/81

-0 i

cm -0.2 5 , , de g-0.4 3 0

3 2-0.6 > 45 60.8 0 8

0.6 3 103 15c D 0.4 3 203 30

._

0.2 . . . . 1.. . I ... ! - 1 - . - j . 3 45I ' / I02.8 ............ 1

. . . . . . .2.4 I2.0 ........... .. ..I I1.6 . . . .c L 1.2 ......F iI 1 iIIj ' . - 1!I!!0.8 . . I : I Ii0.4 I I!1 ! . . ! .. . -!I0I I _fI

-0.4 I - -8- io- 2401. de g

(c) Longitudinal cha rac teri stic s; la rg e radi us vent lip.Figure 10. - Continued.

3 9


42/81

0.04 j

-0.04. . /o1 : I-0.08: - &-

I :

i1,, deg0 00 20 4n 6n 8I3 103 153 203 303 45

-8 1a, de g

(d) Lateral charac terist ics; l arg e radiu s vent l ip.Figure 10. - Continued.

40

c


43/81

. . . . I!0 '3.2/... . 1

l i-0.4 .. . !-0.6 , .0.8 . .. . I".. ..0.6. - - I1I

c D0.40.202.82.4 &2.01.6 - . . I

c LI

i. .!0

-0.4 I - 4a. deg

,+StZ

! . . .I,I

,. .I

!~4-!16 20

0 00 23 4A 60 83 103 151 20> 303 45-... .

-

(e) Longitudinal char act eri stic s; sh ar p vent lip.Figure 10. - Continued.

41

4


44/81

I I I I I I

r0.04. 0 !L

I -0 08-0.12

0.020.01

II O r 0.01 I ._1 .. ] _ _.... 1

I I i 1.... ...-1... . . .tl... -ii I..... .I. -8 -4 4 8 12 16 a, de g

(f) Lateral c haracterist ic s; s har p vent l ip.Figure 10. - Concluded.

42

20


45/81

----

. ~. ... -. . .

I iI;! -1II! II... I-0.2 . ... . _ - l 5 ' de gcm -0.4~-I 1 0 . . 1 2 -0.6 ' * - j - . & > 4 1 6'- . 4 ..0.8 - - - 1 \ 1 8

0.6 iI . !I j .. 110~ - 3 15! , ) 20c D 0.4' . .!1 i

I + ) 30! 5 450.2 ..-. .. I??!-+@ . . . ,.iI0 ' T i - II!I. - . . . .. ,IjI .. . .. ....I!! . . . II!2.8 .. . -I2.4 -. . . i! I1I + II~! I2. O I .. ,L .. i 1i.... .c L lm61 1 - @ . JII . . IjII1.2 ~!0.8 1 I

~1- .. 1 . ... . j i I

Oe4 I II iI !I 4O 1 I i i I I!I-0.41... - ~..-4I 4 12 - 16 20 24(a) Longitudinal characteristics; 6f = 40; x/E = 0.96; sma ll radius vent l ip.

Figure 11.- Effec ts of vent-lip g eome try on spoile r C character i s t ics .

43


46/81

0.040

ct -0.04-0.08-0.1 i

0.020.01

c" 0-0.01- 0.02

0.020.010

- 0.01-0.02

. . .... .- . . .

-_a, de g(b) Lateral characterist ics; 6f = 400; x/E = 0.96; sm al l radi us vent lip.

Figure 11.- Continued.

44


47/81

--

. . . - I i I! !; I : !0 I I, I ; . I-0.2cm-0.4-0.60.80.6

0 20c D 0.4 ~ 0 30

I n 450.2 0 2.82.4 2.c1.6

c L 1.20. a0.40 I IjI - ! /-0.4 4! -4 20 24

a. deg(c) Longitudinal cha rac ter isti cs; 6f = 400; x/C = 0.96; large radius vent lip.Figure 11.- Continued.

45


48/81

0.01 .... .0 ?Ect -0.01 --c

-0. OE -9-4-0.1i

.

0.020.01

c" 0-0.01- 0.02

0.020.01

I d0 - 0.01 .

fPP-0.02 .. ...-i... --8 0 4 8 12 1

a, de g(d) Lateral cha racteris t ics; 6f = 400; x / E = 0.96; lar ge rad ius vent lip.


46


49/81

r j0 1 i -0.2cm -. - -1 '. . .-0.4 II -0.6 1

. ... . .+ . -1.. . .0.2 . / ' 0 I I2.8 .. .. .. .,. .. .. 2.4 &2.01.6 Ic L 1.2 ~ . . . . & q0.8 I ' I *I

iI -0.4 - I -4 a. deg

(e) Longitudinal characteristics; 6f = 40 x/E = 1.00; sh ar p vent lip.F igure 11.- Continued.

47


50/81

- .. I-41 g S , de g

0 0 0 2 0 4 A 6 0 8 n 10 0 15 0 20

a, deg(f ) Lateral character i s t ics; 6f = 400; x/E = 1.00; sharp vent lip.

Figure 11.- Concluded.

48


51/81

0-0.2cm-0.4-0.6

. . . . .0.80.6

c D 0.40.202. a2.42. c1.61.20.80.40

-0.4

Figure 12.- Spoiler A characterist ics with b f = 40; x/C = 0.96; larg e rad ius vent lip.

4 9


52/81

- -

' . II ., . II .. . . ., I . ., . .. .

, I .0 1.CI -0.04 g S , deg

-0.08 0 0 .-o.1zj I - - I . /- . - I .. 1 '.... .. 0 20 4A 6_.I . .. . . . . . . . . .. . - ... .. ..... 0 8 n i o0.02,- . ! . . . . . I . - ' - . . . . . . . . 3 15II 2 20. . . . . . . .0* 011 I t - - - - - . 3 30

. . . . . .

. . - . .. . .

~_ _. . . .

. . .

~-8 -4 0 4 8 1 Ia. deg

(b) Late ral charac terist ics.Figure 1 2 . - Concluded.

50


53/81

, 1

0 8 .. I , ' I-0.2 , _ . .cm . .

I-0.4 . . . . .*0.6.0.8

0.6 . . . . .0.4 . . . 0.2 ........ 4. . .0 . I '

8 .

. I1 1

1.I

i , i IiI....!.A.. !.- . II

I Vented spoiler... _ j . deflection, degc d

...j[ 4

' I : 6 028 4

10 8

2.8 ....... . . . ., ......... . . . . . . - . .2.4 . ,

. . . . . . .2.0 . . .1.6 . , . ,

c L 41.2 . . I.. . . . .0.8 .. .0.4 . . . . . .0

-0.4 - . . . . . . ! ..I 16 .. __ I24

. . . . . . . . .

01. deg(a) Longitudinal chara cter isti cs, deflection sequence 1.

Figure 13.- Eff ect s of se que ntia l deflection of s po ile r B elem ent s b, c, and dwith 6f = 400; x / E = 1.00; large radius vent lip.

5 1

C


54/81

....... . . -. .--. 1 - - -

-0. OE 1 -4Vented spoiler

-0.1: . . . . . . . . . deflection, degb c d.- .... -. . . 0 6 4 0

0.02 - . . . . . . . . . - - O l O 8 4IS 10 80.01 . . . .I...

0.01 . . . . . . .0

cI -0.01 .....

cn 0- 0.01 - .- -_- . . . . . . . . . . .. I :::..- 0.02 .......... .- ........ - .... ....... _...... ._...

0.02 ... -1 ... . . . . -. . - _ ..... .- ..... . * . I _ . . ...-* . .. .0.01 ....... . . ...... ... . _ ..............0 -a- 1 . I . ._.0.01 ... - . . . . . . . . T .... . .._. . _ I . ..... _ .1.....-0.02 -7- .. - I..

1

i- .- - . -.- .12

.-._..-

20... . .

,

I

,

1. I ~- -.I1. . . . . .a, de g

(b) Lateral charac terist ics, deflection sequence 1.Figure 13 . - Continued.

52


55/81

. . . . . . . . . . . .-i ' -1- ~ i I

Vented spoilerdeflection, deg

-. . . .

.....

. . .

. . .0.4 -..- I ..I I ..... 'I 8I112-4 0

a. de g(c) Longitudinal cha ract eris tics , deflection sequence 2 .


53


56/81

-0.121 Ii

0.02 II0.011 +

-0.021 I ~!i : 0.021 - ; Ii I; 0.01;- : I !I !cy 0 j i 6

-0.011I j/*4

-0.021 I 1 : L 2 . -8 -4

. . . I .

- I . i

.Ii T deflection, deg

_ _ . Ii - .- b c d0! 6 - - - ! - 6 10

! . - - &I

--I -Ii . . .,I 17- -

I

4

(d) Lateral char acteris tics, deflection sequence 2.Figure 13 . - Concluded.

54


57/81

---

c m

c D

c L

0-0.2-0.4-0.60.80.60.40.20 . . . . . . .

, .. . , .. . .. . . . . .2.82.42. (1.61.i . .0. E , ..0.4 . . . . . .

....... . . . . .0 .- II. 1 . . . 1-0.1 . . . . .......... 'I .. . 1:'-a 0 12a. deg

1ynamic pressure0 1.44 kPa (30 Ib/ft')0 0.48kPa ( 10 Ib/ft'). . . . . .. . . . .

........... . . . . . .

,L.* 20 1

(a) Longitudinal charac teri stic s; 6 f = 30; x / E = 0.96; larg e radiu s vent lip.Figure 14 .- Effec ts of dynamic p r es su r e on vented sp oil er B character i s t ics .

55


58/81

--

I

, ,,. .--...--. ..-,,, . ,.,,........... .-_---. . . .....

-

0.0I,i1 .- #icr -0.01 + . . . . .

-0. OE . . . 1 . . . . . . - l l.i - . Dynamic pressure-0.1; iI ....... 0 1.44 kPa (30 Ib / f f )

Ii 0 0.48 kPa ( 10 Iblft').- . . . . . . . . .. . . . . .0.02

__ . . .0.01-c" O ft- 03- a

. .....-0.01. . . . . .- 0.02

. . .- . ...... ....0.02. .0.01

0 #@F===....- 0.01

.-0.024 1 20 1 I

a, de g(b) Lateral character i s t ics; 6f = 300; x / E = 0.96; larg e radius vent lip.


56

..... -.... ....


59/81

0-0.2cm-0.4-0.60.80.6

c D 0.40.202.82.42.01.6c L 1.20.80.40

-0.4

' - ! - -

Dynamic pressure0 1.44 kPo (30 Ib/R')0 0.48 kPa ( 10 Ib/ft')

(c) Longitudinal cha rac teri stic s; 6f = 400; x / E = 0.96; blunt vent lip.Figure 14.- Continued.

57


60/81

- -

1- IiI a.. . . . . . . . . . . . . .-0.08 . .- c .... - . . . I .-Dynamic pressure

. . : . .i . . - - ..-0.12 i 0 1.44 kPa (30 I b W )i IJ 0.48 kPa ( 10 Ibift')_- . ~ . .~ - ,..

0.02 . . . . . . . . . . . . . . .0.011 - ...........

c" +'. .

- 0.02 . . .i..!I0.01 i . , .[--1

cy O k&- 0.01 ;&

I-0.02 .... ; .

II. I-8 20 4

(d) Lateral character i s t ics; 6f = 400; x / E = 0.96; blunt vent lip.Figure 14.- Continued.

58


61/81

-. .. . .

0 - - Ti.. -,-0.2 ..... .*. ...... . . .c m -0.4 ... . . . . . . . . . . .IC -0-0.6 .- .. - .. ._ . . . . .

. .0.8 . . .. .0.6 - ._ . . - -. . . . .

A. .0.4 . . Dynamic pressure

0.2 . . ... . . . - 0 1.44 kPa (30 Ib/ft)0 0.48 kPa ( 10 Ib/ft)-- I L__0 I2.8 .. - . ... . - - ..... .. .i2.4 ... . . . 5 0 . . . . . . . . . 1

. . .... . . . .2. c - - -I I1.6 1 . . . . .

cl I 01.2 1 . . . --..I0. E k

If /

.. . . . .0. I . . .0 .- .

-0 .1 .....a, deg

(e) Longitudinal cha rac teri stic s; 6f = 40; x/E = 0.96; larg e radiu s vent lip.Figure 14.- Continued.

59


62/81

I

- . . _. . _ . . - _.

-- . .QFQP Q7_ . . . . . . . ...... ........... .,..1 '. . .

. - _. - .. . . . . - . . . . . . ....... ... - .. 0 1.44 kP a (30 Ib / f f )

0 0.48 kP a ( 10 Ib / f f )- - .- .... . . . . ..... _ - .. . - .

%= w s'. . ....... _ _. . . . .... - . .

....... . _. . . . . .. .. .. . . . . . .- ...-0- 3-

..... . . .

c-. . - . ?0 24

(f) Lateral character i s t ics; 6f = 400; x/E = 0.96; large radi us vent lip.Figure 14.- Continued.

60


63/81

--0 I1 . - - i ' I-0.21cn l-0.4 I-0.60.80.6

% 0.40.20

. .2.82.4 92.01.6c L 1.20.80.40

-0.4a, deg

(g) Longitudinal c har acte rist ics ; 6f = 400; x/E =Figure 14. - Continued.

. ... Dynamic pressure0 1.44 kPa (30 Ib/ft*)

-- .-1 0 0.48 kPa ( 10 Ib/ft')

I. .

12

1.00; la rg e rad ius vent lip,

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. , *

. . . . . , .

-0. . . . . .

- ....

I; -=. - ,I. ...JDynamic pressure

. . . . 0 1.44 kPo (30 Ib/ff)

1--.I... .... ..- . . . . . - 0 0.48 kPa ( 10 Iblft')QF ... . . . . . . . . . . .c" 0: : ~ ---I4 . .- 7

,-0.01 - . . _ . . ..... . . . . . . ~- __ . . . . . . . . .. . . . . .....0.02

. . . . . . . . . . . . . . . . . . . .

. . . . . . . . . . . . ... . . . . . . . . .2--a I..T-c . . . . . . . . . . . ....1. ._ .. ... ,

1 I

. . - - .1. . . 1. - ......_

1

a, de g(h) Lateral character i s t ics; 6f = 400; x/C = 1.00; lar ge ra dius vent lip.


62


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0 i -_ II-0.2c m -0.4 -0.60.80.60.4

2.82.4 1:2.01.-,1.6

c L 1. ' ' .

-0.4 I l 40a. deg

(i) Longitudinal ch ara cter isti cs; 6f = 40; x/E = 1.00; blunt vent lip.Figure 14. - Continued.

6 3


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0.040

cz -0.04-0.08-0.12

0.020.01

c n O-0.01-0.02

0.020.010

- 0.01-0.02

( j ) Lateral character i s t ics; 6fFigure 14.

. . . i . . . . . . . . . . . . - .I Dynamic pressure

.... ' -~ 0 1.44 kPa (30 Ib/ff)- j _ -. , . 0 0.48 kPa ( 10 I b / W

8 12 16 20 24a, deg

= 40; x / E = 1.00; blunt vent lip.- Concluded.

64


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I --

0c m-0.5-

I

Oa6I0.4

cD0.2

0 - I2.5

I

2.0

1.5cL i

.o0.5

I

O II-0.5 -8 -4 0 4 8a ,deg

.70

.92.96

1.oo....

. ..

. . ~~ ~......

.___ _-1 .., -,

- 24Figure 15. - Effects of se ve ra l flap position s and deflections on longitudinal

characteristics of wing.

65


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--

0 ;. .

cnl-0.5 &.. ., . . .0.6 . .! '0.4icg I .

0.2 ii! *0 :

_ _ ~ _ ~2.5

2.0

1.5c L

1 .o--f#. .0.5-

. . .0

-8 -4

X-d,,degA 40 1.ooh40 .96

i'a' I

j l! ;I !

- 4 8 12 16 20 24a , degFigure 15. - Concluded.

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0 2 6 8 1 0

I .I

dS ,deg(a) 6f = 00; x / E = 0.713.

I !

I

Angle o fBack, deg1 4Y O > 43 8

45

Figure 16.- Effects of flap position and deflections and angle of a ttac k on rol ling mom ent sgener ated by deflecting spoiler B with lar ge rad ius vent lip.

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An, 3 aattack, de(0 - 4

0 2 4 6 8 1 0 20

(b) 6f = l oo ; x/E = 0.917.Fig ure 16. - Continued.

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-0.14,I

1 i ~-0.12 i!i

I I jj,i

I I -0.10 I I i 1 Angle o f

-0.0% ittack, deg0 C 2 4 0

-0.06 I j I 1

-0.049 i

-0.0: i F!

//b.'/ 6 4

0 I II I 1. 30 4 5 (e ) 6f = 3 x/: = 0.960.

Figure 16. - Continued.69


72/81

. . .

II c'/i!II b 1 attack, degl o -4

'!1 l o O0 4j ja a1!

. I . . / 1 ..i ...I. .1. . . . . ...........i . . .. . . .I:. . . .i ' ;.;I :.I ',i! I .:i :j : . . . ...... ,. .......! ..:.I..{:;II! . 1....I, i , ..

!II

: i! jij i!! j I

t ...I l l

.I. I -I 15 4

(d) 6f = 400; x / E = 1.00.Figu re 16. - Concluded.

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- 0 . ~ ~ 1 i!!-0.121,

i1 . II '-U . lO \ I

I Ii , i-0.081

I

C !2 1-0.06l I J-0.04 i/ ent lip 0.%40 Blunta Small radius .96

0 Large radius .%-0.02 I Ih Large mdius 1.mBlunt 1.wFi0 I I I 115 2( 30 4 5

(a) CY = -40.Figure 17.- Eff ect s of vent-lip geo metr y and angle of attack on rolling moments generated

by deflecting spoiler B with 6f = 400 an d x /E = 0.96 and 1.00.

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Il j

4 j4

i Ii

A i f+i/r j4

i Ii j ii i i

I /Vent lip. .

, . '0 Blunt 0.NEl Small radius .%3 large radius .%5 large radius 1.00n Blunt 1.00D IT 1 20


72

I


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. .

-0.14 iI ii

-0.12

jII

-0.10I I I

I i1-0.08 j J I ~C2

-0.ociii IIiI. i i

-0.04 iIj

I

-0.0:

0 FitIc

~~~ , .. . .. . .

.. .

Vent lip -c 0 Blunt 0.W EI Small radius .%@ Large radius .%A large mdius 1.00h Blunt 1.ooO M 1.oo

4s 4 6 1 0 20 30

Figure 17 . - Continued.

7 3


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I

I

I

I

6 8 10 15

Vent I' 0 Blunt

Small radius@ Large radiusA Large radiush Bluntoshorp

30

-c0.%.%-96

1.oo1.oo1.w

(d ) CY = 80 .Figure 17.- Concluded.

74


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iIiI

#'iI

I/'! 'I I IIii

-0.04 ~ IV en

0 Small radius 0.w-0.02 I3 large radius -961M)

4

iiI0 j 1- -ij

4 6 8 1

Figure 18.- Effects of vent-lip geo met ry and angle of attack on rolling mom ents gen era tedby deflecting sp oile r C with 6f = 400 and x/E = 0.96 and 1.00.

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#

/

d J

5 I ,

I

j' I -E

j Small radius 0 .%Large radius .%ii I 1.00,/1 i 10 20 45

6, ,deg (b) a = Oo .


76


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-0.14

-0.12

-0.10

-0.0I Ax

CI ;iI A-0.06' /1 4/I

-0.04'

-, @ Small radius O.%lI t large radius .%-O*O2I

i I0 I l l15 D

6 ,deg( c ) CY = 4 0 .


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-0.14

-0.12

-0.1 0

-0.08

5 -0.06

-0.04

-0.02

Angle o fattack, deg0 - 4 0 0 0 4A 8

p,degFigu re 19.- Effect of angle of attack on rolling moments generated by deflecting spoil er A

6f = 400 and x/E = 0.96.

78 NASA-Langley, 1976 L -10736


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