NASA NACA-TN-702-1936 Wind-tunnel tests of several forms of fixed wing slot in combination with a slotted flap on an N A C A 23012 airfoil《固定式翼缝和在N A C A 23012机翼上开缝襟翼若干形式的风洞试验》.pdf

1、: l 1 3 .- I -P TECHNICAL BOTXS NO. 702 i - WIND-TUNNEL TESTS OF SEVERAL FORtiS OF %!C w-sL+-: .-I -.- ; . _ . . ._ _. . IN COMBINATION WITB A SLOFm FLAP OB Ax . L; L-: -. _. By M. J, Bamber Let ngley Memorial Aeronautical Laboratory N.A.C.A. 23012 . . _- _ . . ._ .L _- _ - -.- - I _._I. .-. .“- - ;

2、 - . -. _L - - _. A , . ., . ;- _ 1 -.-.- - _ - . - .- - z- ._-_ . I_-. - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 . . _-. : :. _ ;. -. .Y UTIONAL ADVISORY COMMITTEE FOR AERONAUTICS TECEIIICAL NOTE SO, 702 JIZD-TUNNEL TESTS OF SEVER by lo-fo

3、ot mind tunnel. The airfoil 0xtendea com- pletely across the test section so that two-dimensional flow was approximated. The model nas fitted with a full- span slotted flap having a chord 25.66 percent of the air- .- foil chord. The slots extended over the entire wing span. m-Z The wing-s lot locati

4、on was varied along the chord and several variations of slot gap and width were tested at each location. i The data are presented in the form of tables of imi portant aerodynamic characteristics for each slot tested and as curves of section lift, profile-drag, and pitch- -ing-moment coefficients. th

5、rough the slot is given. The relative air velocity % - .I i .a-., _ ._ A slot as-far back on the airfoil as the 55-perCent- chord point, with the flap deflected 4Q“, was Practically ineffective for increasing either the maximum lift Cocffi- cient or the angle of attack for maximum lift. A slot near

6、the leading edge of the airfoil, with the flap de- fleeted 00, increased the maximum lift coefficient by 0.65, : the maximum angle of attack by ll“, and the mfnimum pro- fileTdrag coefficient by 0.012. ! 400, Wfth the flap deflected : this nose slot increased the maximum lift coefficient by 0.40 and

7、 the maximum angle of-attack by loo. ! - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 .- N.A.C.A. Technical Note No. 702 INTRODUCTION If tha stalling of the wing tips of highly taper-ed wings can be delayed to a hZgher angle of attack thap that

8、of the center section, the lateral stability and the useful maximum lift coefficient of-the wing will be great- ly improved. Various-methods have been used to make the tips of the ,wfng stall after the center section. Some of these methods are: changing the airfoil section along the span, washout at

9、 the wing tips, and -either fixed or mova- ble wing slots. If a change in the airfoil section alcng the span and washout 8re to be effective in delaying the tip stall with highly tapered wings, they will probably give poor aerodynamic characteristics in the high-speed and the climbing ranges, Leadin

10、g-edgc slots over the tip portion of the wing appear to give the most- practical SO- lution of the problem because thdy have little effect on the span lift.di;tributian for the high-speed and tha climbing ranges. Movable slots give a large increase in the angle of attack for the stall and an increas

11、e in the maximum lift coefficient. Fixed slcts give about the same increases in the maximum angle of attack and the max- imum lift coefficient as the movable slots, but they con- siderably increase tho minimum drag coefficient (refor- ences 1 and 2). The fixed slots, however, are simpler to : constr

12、uct and are less likely- to give operational troubles than the movable slots. The purpose of this invsstigat5on was to datermine the effect of some fixed-slot parameters on tho aorcdynam- ic characteristics of an N.A.C.B. 23012 wing with a slot- ted flap. One of the slottod-flap arrangomants roporto

13、d bn rofcronco 3 mas used bocausothat arrangonont appear6 to be ono of tho most promfsing high*-lift dovices dovol- opod up to the. prasont time. The slots wcro varied in po- sition along the chord, in gap, and in width. Tho data given in reforoncos 1 and 2 for a Clark Y section were usod in choosfn

14、g the slot, forms and tho slot locations. APPARATUS AND TESTS The airfoil was built to the N.A.C.A. 23012 profile with mooden flap-and flap-slot forms. The intermediate aaction of ribs was covered with tomporod waterproofed wallboard, and the slot forms mere made of wood and metal. . . 1 c Provided

15、by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-N.A.C.A. Technical Note,No, 702 3 . * n The model has a 3i-foot chord ,and a-7dfoot span. The - chord of the full-span fla_p is 0.2566. The airfoil sro- file, the dimensions of the flap and the flap slot, and th

16、e lccations of the flap nose when the flap Is defiected are given in figure 1. Figur*es 2, 3, 4, and 5 show the fixed-slot arranr;ements with their locations Lnd dimen- sfons. The full-span slots were desfgne-d to give systea - natic varfations in gap and width for slat chords of 0.55c, 0.205c, and

17、O.l29c, for ono slot. The other slots were obtained by combinations of slat and slot forms. The pletely spanned the closed test section of the wind tunnel so that two-dimensional flow 17as prsc-. tically attained. (Set roforenca 3.1 The velocfty of the air flow through the slot was measured by two l

18、/16-inch-diameter impact tubes located - -.- in the smallest part of the slot, one on each side and about one-fourth of the gap from the sides ofthe slot; the static reference -oressure was obtained with a l/16- inch static tube in the middle of the- slot rounded iotieredge. _ - . - - - ., / - - - _

19、 - - -.- -.- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. 5 i I . .h I 0 $11) I I I illlllllll 0 .J .4 .a .a 1.8 1.0 I”“UC I.P 9.4 P.b -.B , Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. , Pr

20、ovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-* c t b * - - . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-* c *I t .J 0 4 ” .sI ! ! ! ! ! I ! I ! ! ! ! !-!-+-I ! ! 1.8 amtl2llft Q18%; a.0 s.a n.4

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22、 i i i iW A/ 1 .4 .I .I 1.0 1.a 1.4 1.6 1.8 1.0 a.1 1.4 a.6 8ati.xl lLft ObdYioLrM, or Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-N.A.C.A. Technical Note No. 702 I Fig.12 1 . . 24 20 18 16 14 12 w-3.17, 3.13, 3. , 4.1 16.01 & e-2.83, 3.17, 3.16,

23、 3.94 12.8 t 1.p -+o I 0, 2.00, 3.00-so 1 I I I 1-t I- I I I I I I ! I I 16 24 32 40 48 Slat &hord,percent cw Figure lZ.= Variation of angle of attack at maximum lift With slat chord. 6f, O“. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-N.A.C.A. T

24、echnical Note No, 702 do at c -.t-tt-t 18 %2.8 ,t I I I I I 0 I I I t OT-2.$9 =-2. 0 l4 .%2.57 9- 1.K ! 4 -1 . I 1 Fig.13 - I 2.00, 3.00$ 1.00, 2.00P 48 56 Slat chord,percent cw Figure 13.- Variation of angle of attack at maximum lift with slat chord, 6f, 40d. Provided by IHSNot for ResaleNo reprodu

25、ction or networking permitted without license from IHS-,-,-N.A .:.A. Technical Note No, 702 Fig.14 60 .4 .6 Gap-width ratio Pigure 14,- Variation of =1 nlax cd0 (at cl= 0.3) with gap-width ratio. Sf, 0. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-N.A.C.A. Technical Mote No. 702 Fig.15 U .2 .4 .6 .8 -1.0 Gap-width ratio cl - JY.gure 15.- Variatipn of max 6-f, 4o“. cd0 (at.0 I= 0.3) with ga&nkIthratio, _1- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-