NASA NACA-TN-719-1939 The effects of partial-span slotted flaps on the aerodynamic characteristics of a rectangular and a tapered N A C A 23012 wing《部分展翼的开缝襟翼对矩形和锥形NACA 23012机翼空气动力.pdf

《NASA NACA-TN-719-1939 The effects of partial-span slotted flaps on the aerodynamic characteristics of a rectangular and a tapered N A C A 23012 wing《部分展翼的开缝襟翼对矩形和锥形NACA 23012机翼空气动力.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TN-719-1939 The effects of partial-span slotted flaps on the aerodynamic characteristics of a rectangular and a tapered N A C A 23012 wing《部分展翼的开缝襟翼对矩形和锥形NACA 23012机翼空气动力.pdf（11页珍藏版）》请在麦多课文档分享上搜索。

1、AUG4 %I3 -.- TEGBNICAL NOTES I, . ii I i NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS _ - NO. 719 . ; TEE EFFECTS OF PARTIAL-SPAN SLOTTED FLAPS ON THE AERODYNAMIC CHARACTERISTICS OF A RECTANGULAR AND A TAPERED N.A.C.A. 23012 SVING By Rufus 0. House ._ -.- Langley Memorial Aeronautical Laboratory _-:

2、7 .- -.- - - . . ;-.i - . - :- . .,; . . 7. .- Washington July 1939 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS M-P TECHNICAL NOTE NO. 719 THE EFFECTS OF PARTIAL-SPAN .SLOTTED FLAPS ON TEE AERODYNAMIC C

3、HARACTERISTICS OF A RECTANGULAR AND A TAPERED N.A.C.A. 23012 WING By Rufus 0. House SUMMARY An investigation was made in the X.A.C.A. 7- by lo- foot wind tunnel to determine the aerodynamic characteris- tics of tapered and rectangular wings with partial-span slotted flaps, Two N.A.C.A. 23012 airfoil

4、s equipped 5th center-section and tip-section flaps were tested. The r8SUltS showed that the changes in lift and drag due to changes in flap span for both rectangular and ta- pered wings having partial-span slotted flaps were similar to those for corresponding wings having partial-span split or plai

5、n flaps. For the two wings tested, higher values of maximum lift were obtained with center-sectfon slotted flaps than with tfp-section slotted flaps of the same sise. The highest values of lift-drag ratio at maximum lift for the rectangular wing were obtained with oenter-section flaps and, for the t

6、apered wing, with tip-seotion flaps. Oenter-section flaps on the tapered wing gave higher values of drag at maximum lift than tip-section flaps: no great difference in drag at maximum lift was apparent for either center-seatfon or tip-section slotted flaps on the rectan- gular wing. INTRODUCTION ! 1

7、 Wing flaps are used on many present-day airplanes as a means of increasing the speed range. Partial-span flaps are employed in nearly all cases because part of the trail- ing edge is usually requfred for lateral control. Investigations have been made to determine the effects on rectangular and tape

8、red mitnqs of partial-span split and plafn flaps. The results are reported in references 1, 2, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 N.A.C.A. Technical Note No. 719 and 3. The present investigation deals with similar ar- rangements of slo

9、tted flaps. APPARATUS AND TESTS Modela.- The models used in these tests were built of laminated mahogany to the N.A,C,A. 23012 profile, each model having a span of 60 inches and an aspect ratio of 6. One wing is rectangular in plan form (fig. 1) and the other is tapered 51 (fig. 2). Por the tapered

10、wing, the NA.CA. 23012 profile was used at all sections along the span and the maximum ordinates of all sections were in a horisontal plane on the upper surface. The flap used is the N.A.C.A. slotted flap 2-h de- scribed in reference 4. It was cut into sections to form 10 flaps of equal span. The fl

11、ap angle was measured fn a plane parallel to the plane of symmetry. . tunnel.- ITin whereas, for the tapered wing, the maximum lift and the drag at maximum lift were greater and the lift-drag ratio was less with center-section flaps than mSth tip-section flaps of equal span. It should be borne in mf

12、nd that the point along the . span at which the stall begins may have an apprecfable effect on the value of the maximum lfft obtained fn flight. If the tips stall first, any further increase in angle of attack is limited, although ft may be several degrees below the angle at which maximum lift is ob

13、takned 9n a nfnd tun- nel. Consequently, some of the values of the maximum Zift coefficient given for the tapered wing and for the rectan- gular wing with center-section flaps may be somewhat higher than those attainable in flight. Langley Memorial Aeronautical Laboratory, National Advisory Committe

14、e for Aeronautics, Langley Field, Va., April 25, 1939. 1, 2. 3. 4. REFERFXCES House, R. 0.: The Effects of Partial-Span Plain FIaps on the Aerodynamic Characteristics of a Rectangular and a Tapered Clark Y Wing. T.N. No. 663, N.A.C.A., 1938. Wenzinger, Carl J.: The Effect of Partial-Span Split Flaps

15、 on the Aerodynamic Gharacteristfcs of a Clark Y wing. T.N. No. 472, N.A.C.A., 1933. Wenzfnger, Carl J.: The Effects of Full-Span and Par- tfal-Span Split Flaps on the Aerodynamic Character- istics of a Taperod Wing. T.N. Ilo. 505, N.A.C.A., 1934. Wenzinger, Carl J., and Harris, Thomas A.: Wind-Tunn

16、el Investigation cf an N.A.C.A. 23012 Afrfofl with Var- ious Arrangements of Slotted Flaps. T.R. No. ,664, N.R.C.R., 1939. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . 1. 6 R = .789”-, -. . 370 . L .B = .811“ I , , . I , -s :, 8 -L-_ - -_ ,

17、L _- - - - - *- ,475 8.081 bRTs c = 10.00“ Blgure 1.“ N.B.C.A. slotted flap on the rectangular N.A.C.Ai 23012 ring. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-f a- t I- L . l . I * . 1 b -= 30.00“ 2 IFigure 2.- N.A.C.A. slotted flap on the 5:l t

18、apered N.A.C.A. 23012 wing. .58“ I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-P.A.C.A. Technical Mote PO. 71d Flgr. a.4 a.4 I -58 I I I t I I I I t t I I t t t I I -4 0 8 LB -16 -8 0 . 8 16 Anale cf rttaok, a, deg. - _. Pigum a.- vL?iixon of 1 A

19、ngle of l ttaok, a, dw. Qltohin qg-mc,ed:d%iei% with Tigure 4.- Variation of lift, dr8g, and pitobing-mommnt ooeffloienta with anale of attaok. a knter-section a1ott6d fla on-the rectangular 1l.A.O.A. 2301;) ti. i#) 40 60 80 100 Flap Pm, peroent ting spsn fiigure 6.- Xfeot of w lmqth on Oh, at Oh, a

20、nd on L/D rt on OD rlgure 8.- 0 Xfwtof flrplengthonO, onOp at 0 bsr and on L/D at 0 Raotangulsr H.A.0.A. sol2 ring. fbf 8: tkparsd P.A. . . aim8 ring. bf Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4.0. fe0m0il rote IO. ne Flga. 6,7 a a 1 yg” rm

21、span 0 :80 P-.40 - x-Jo .a- &O +-0 . r1gnre 6.- Variatlcin of lift, drag, and pitohlng- went ooeffioients with mgla of Plgurr 7.- Variation of lift, drpg, and T-= ment oosffiolent6 rlth attaok . Oenter-naotlon rlottad flya an the 5:l tapered 1.A.o.A. atma ring. Sf-10 angle of atE%f“T p-saotlon mlottad flap8 on the f5:l tapered I.A.O.A. a3018 wing. 61-e Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-