1、NATKMAL AyRY COMMITTEE FOR AER,.ORIGINALLYISSUEDJuly1941aeAdvanceConfidentialReportWIND-TUNIWELINWEW?XATIONOF PERFORATEDSPLITFL - “ “. .By Paul E. Piirserand Thomas E. !l!urfierSUMMARYAeroQnaaio charaoterigticg of a rectangular HACA23012 airfoil with ginle and double perforated split flapshave %een
2、 determined In the EACA 7- by 10-foot wind tunnel.A lar:hilolat-eral control may b obtained with a plain aileron.behidsingl oplit flaps, the atleron i effecti?cly blanketed .ad ronderod usoios bchlcd douhlq split flps. Additionalte8ts are recommended to d.evoIo a atiafactor? latel-control device for
3、 use with the perforated doule-oplitflaps.INTRODUCTIONThe IJACAhas undertake an extensive investigationfor the purpose of developing devices suitable for limit-iEg the diving speeds of airplaaen. A a part of this in-vestigation, a stuv has been nade-of test results obtainedd.urinthe development of o
4、ontho airfoil and flap WaS scaled vith CC11U1OSO tape. Plnin-flap doflootion were.nontyurodritL rescct to tho r.irfoil.chor,dlio. .Ulcd !lhunei.cmdEquipnentProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3that danlo pressure could be recorded at l-in
5、ch inter-val-oalong a vertical line 27 Iricheslong yhioh ?as locatod30 inches (3,0c) behind the quarter-chord point of “theair-foil an 5 inches (0.5c) to the right of the plane of sym-metr. This position was believed to be representative ofthe locatio.of tlastrut interferenod arid”tareswere,.relativ
6、el,v.small, these correctionalwere applied OnXY *0the plain-airfoil tits; The standard-jet-boundary o.o.vQc-tions which were applied to all thd forcetetatdata, are:nwhere G is the Jet croeo-eectional area. A value of8 = 0.112 for the closed-throat”wind tunnel was used Incorrecting the reeults. It sh
7、ould be noted ihat, owing to“ the various span-load distributions of the airfoil withthh various split-flap arrandemszts, theso cobrctlons arenot strictly applicable to all of the data. No correctionfor tunzel effect has been applied to the wake locatio.This correction Ig small %ecase of the relativ
8、ely smallmodel used,Double Split lnpS “Tho aoro ezd thews.kcchnractoristics nro shorn as curves of dcamic proH-surc ratio, dqo. plottod anicst dist=co nboo cmd be-low tho extocdod chord lino of the airfoil.Tho results prose=tod In figures 4a a=d 4b show theoffoct of the airfoil trailing odeo aad of
9、the flap porfo- “ratlozs on full-spa and partiml-opan double split flaps.Ronovi=-nnic charac-teristics than did the tester-noctio flaps.Tho romzl.”tsin figures 10m throh 21ELldicated thattho fprnulc devclopod for the pro(ticti.oof drsg cocffi-cicats “due.to the doublo split flmp? uas not diroctl ap-
10、plicnblo to tho sinlo split flaps.The relationship-bet:ee drab coefficleat, riag load-ing: ad idicatod velocit$ for a= airplaEe in a Tertlcaldive is.shorn in fibure 22. Yor other diving aglss, thevelocity Given on the chart should bo nultip”liedby thesquare root o? the site of the ;.-“lIACARep. I?o.
11、412, 1931, ., .-.: . 1.”,.:,.m:-,-7 Tensing-with , “!“-.Varloua Arrangement of 910tted Flaps. - ;.,“”:EACA Rep. No.,664, 1939. .“ . . . .I-1- 1-1- m mProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- .ttAcA .2(2* + ,mt. -A .60+ 4 .L3q -A I.00*Segm*nt
12、/2 3 * I sFig.1I . .I I I I IA.fnuel r /0-by 60- hch recttmg/ with 6?.20cperforutd sit f)eps. Per a.W-inr-m I U7-t-l.B*. D oa$, Ill.H-t-u- P.gC DrOg coefficient, C.;.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CA m11111-“-flap i -+bkseqment /7nu
13、mbers./$bE *E+0 / P -.08/ g/ “-4 / “ .04/N 4- K-/-8 -.2 0 .2 .4 .6 0.8 /.o /.2 /.4Lift coefficient f, CLLg. bGbba)*$Q.-20-40-60-809/90Figure5b.- Effect of various arrangements,of 0.20c partial-span perforated double split flaps locatedO.EOC from the airfoil leading edge on the wake characteristics o
14、f a 10-by 60-inch rectangu-lar NACA 23012 airfoil. 6fU,60;6fL,600./-70/2010080o$40:$20$0-20-40-60q/9.Figure 6b.- Effect of O 20c partial span enter-ection perforated double split flaps located 0.80c from thoairfcil leading edge On the wake har=eteistics of a 10-by 60-inch rectangular NACA 23012 air-
15、foil. 6fu,600;5fL,6!)oProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-UACA./20i6A I l_-4- 1 I I ,VPIAYATX7 / I 10 I13H.08LAIIII III L-r I I I I .04-.2 0 .2 .4 .6 .8 /.o 12 /.4 -Liff coefficient t, CLTiure 6a.- Sffect of O.ZOc rt ial-opm ocnter-eotion
16、 perforateddouhl. a71plit flapa located 0.800 fromthe airfoil leading edge on the aerodynamic ohuaotoristios of s lo-by 60-inoh rectanguhrITACA2S012 sirfoil. 6fu,600;6fL, 600.1111111I I I Ill II I I mmProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-a
17、3z3fEHi”I.80c P +% (I!14 -1 1-1-LH-+ER”7”?.36.3220 .28G-,/-dF/2 + .% _a- - d, *. 1k-/5 4b?.20Q.16“JT37-.2 0 .2 .4 .6 .8 Lo /.2 /.4 -L if+ coefficient, CLigure Ta.-Sffmt Of 0.600 mtlal-mpan tip-neaiiomperforated doublo apllt flmp- loaated O.80c frm theairfoil 1mding edge on the modye obuaot erictics
18、of a 10-by 60-imoh rootmgular IMA3601a tirfoil. 6fu,600;6fL,600.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA Figs. 7b,Etb7!1I I I I0 ?.4.6.8 10 0 .2.4 .6.8 !0 0.2 .4.6.8 /0 0 .2.4.6 .8LO160/m/20200-20-409/90Figure 7b.- Effect of 0.20c partial
19、span tip-Section perforated double Split flaps located O.EIOcfrom the airfoil leading edge on the wake characteristics of a 10-by 60-inch ret- .tangular NACA 23012 airfoil. 6fu,600,6fL,600.K;flop span, /40w enfoil spun2 :_ g f20-204 #j -/00: 100t-jo p-section flopsA Cmter-mfkn Ht+tddT80?3,I I I I I
20、Figure 8b.- Effect of flapspan on theenvelopes of the wakecurves below the stall ofa 10-by 60-inch rectangu-lar NACA 23012 airfoilwith 0.20c perforateddouble split flaps locatod0.80c from the airfoilnImll-mm -,.,.,.,.-Provided by IHSNot for ResaleNo reproduction or networking permitted without lice
21、nse from IHS-,-,-Angle of oitack ofzero lift dL, ,degPitchinq-momenf coefficientMaximum lift coefficient CL.OX at zero lift, Cmc /.O .1PmiProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-XAOA rig. a-40;Q-60$-80-/000 .2 .4.6 .8LO 0 .2.4 .6.8 LO -/209/9
22、0Figure 12b.- Effect of a 0.20c perforated singlesplit flap located 0.30c from theairfoil leading edge on the wake characteristicsof a 10-by 60-inch rectangular NACA 23012 air-foil.9/9,Figure 14b.- Effect of gR7 between airfoil Wface d flap on the wake characteriaticg of a 10-by 60-inchrectangular N
23、ACA 23012 airfoil with a 0.20c full-span perforated single split flap locatedO.20c from the airfoil leading edge,.6fL,900.-,-.,-,-,.,.-.,.-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I1*.,?18.I I_-.1QE. 1co - -,.? s c1 O-+* + - pk$(J-. I6fL, dego
24、A 3:0 60/6 %12 /8/ yd .24-. F “ .b u“+44 =-. _ /- *a .20c1. A -=+.16 Q/ /*.$ d/ / / $b /,.2-A u-4.12 / , ./ 4 0/ /g-8 d p e “ -E-!6-.2 0 .2 .4 .6 .8 /.o L2 /.4 oLif+ coefficient, CLFigure 12a.- Effeotof a O.c full-span perforatad sile a73plit flmp locatef 0.300 from the sirfoil le8d-ing edge on the
25、a71arodymemio oMrsct eristiomof a 10+ 60-inch rect lACA 2S012 &irfoil.v I I 77K-L.4_+L4-+Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-XAOA Fig. 12aI I -.Flop location, percent chordligure 13a.- Effeot of flap loomtion on some of the aerodynamic obmteristia of a 10-by W-inch reot-UMU OA 23131rfoi tith a 0.200 full-wan perforated cincle a71plit flap.-,- .,- ,.,.,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
