1、IQ1,Ii.1+NATIONAL ADVISORY COMMITTEEFOR AERONAUTICSTECHNICAL NOTENo. 1738WIND-TUNNEL INVESTIGATION AT LOWCONTROL CEJARACTEXUSTICS OFSPEED OF THE LATERALAILERONS HAV3NGTHREE SPANS AND THREE TRAILING-EDGEANGLES ON A SEMISPAN VKNG MODELBy Leslie E. Schneiter and Rodger L. NaesethLangley Aeronautical La
2、boratoryLangley Field, Va.WasljngtonNovember 1948-. . . - . . ,._IProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECHLIBRARYKAFB,NMNATIONAL ADVISORY COMMITTEE FOR AERONAUTICSHKKKtCAL/NOmNO. 1738WIND-TUNNEL INvXSTIGATIOMAT LOW SPEED OF TEE LATERALCON
3、TROL CHAXWTEEUSTICS OF AIXERONS HAYINGTE!REESPANS AND THREE TRAILING-EDGEANGGES ON A SEMISPAN WING MODELBy ljese E. Schneiter and Rodger L. NaesethA wind-tunnel investigationhas been made of the low-sybed lateral.ccmtrol characteristicsof a tapered, low-hag, sasx * model eP-ped with 20-percent-chord
4、sealed ailerons having spans of 0.$54,0.583, anti 0.294 percent of a full-span ailercm, each with sfiscripts 1, 2, 3, a71 “o “ catestations at which pressure measurements are made (fig.2)twice drag of semispanmodel a71rollhg moment due to aileron deflection shoutx-axis, foot-jounasyawing moment due
5、to aileron deflection aboutZ-tis, foot-poundBaileron h5nge mcment, foot-poundsfree-stresm dynemic pressure, pounds per square foottwice mea of semispan wing model, 17.54 square feettwice span of semispanmodel, 10. feetaspect ratio of wing, 6.23()b25wfng mean aerodynamic chord, 1.745 feet. . - . . -
6、-. . - - - ,.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-IiACANO. 1738 .cM2baI)atYxvPai5a$Czpu%local wing chord, feet5area moment o aileron behind and about the hinge .axis, feetdistance along X-axis from leading edge of root chordto leading edge
7、 of mean aerodynamic chord, 0.254 foot:2c=) span of aileron or flap, measured prallel to Y-axis, feetspan of full-span aileron or flap, measured parallelto Y-axis, feet wlateral distance fran ane of symnetry,measured parallelto Y-axLa, feetlongitudinal distance from leading edge of wing-root chord .
8、to wbg leading edge, meased psrallel to X-axis, feetfree-stream veloci, feet per secondmass densi of air, slugs per cubic foot.angle of attack of wing with respect to chordylane at root of model, degreesaileron-cleflection angle relative to chord plane of-, measd fi a PF perpc* to aileron-,hinge tis
9、 and yositive when trailhg edge is down,degreesaileron trailing-edgeangle, measured In a planeperpendicular to aileron hinge axis, deeesrolling-moment coefficient produced by 1 differenceh engle of attack of various right and left prtsof a camplete wing (reference1)effective change h angle of attack
10、 over flappedpart of a wing produced by a unit change in flap ,deflection,- - ,. , -”T “., -. .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN NO. 1738.#/ 5.a71c)asChb = e. a()acLcLa = %- a()acc8 = A = 6.23;taperratio= 0.49. (Alldimensionsare
11、inftexceptas noted.). .,- ,- .-. . .- -.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TNNO. 1738 S2414.593.93”- i2.+2 -+tFigure2.- Locationofpressureoficeson semispanW rnodeL(Alldimensionsareinft.). - ,-_ . -,.-Provided by IHSNot for ResaleNo
12、reproduction or networking permitted without license from IHS-,-,-.Figure 3.- Semispan wing model mounkd in Lfuey WI MPH -by 10-foothmnel.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.-, .-T .-, . .- ,- - -, - ., “. -. . . . . . .,Provided by IHSN
13、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1738I17,Pue- contour ajleron (N AC A651-02? atrfoll .secfo), = 6Stpaqht- side aflepw, =/4”. .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 173
14、8.02T-.01-02 -30 -20 -100 !0 20 30Aileron aefleciim ba = 0.95ba; = 6._._._. . - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.24 NACA TN No. 1738 .,A.2.1.0 -1,-2-3 .-?430 -20 -10 0 10 20 30Aileron defkcfiw, . - - .= . - - - -.,. ,. ., ,.-,-Provide
15、d by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA NO. 1738 25,i.z./34/()-4:64.2P31 ,* II II IIJI-illL3-(deg)v -4.3oA 4.30 8.51 12.7 . :“ /,21.2.8AlUwi”-i7 u%)l I i ifl io8 44Y I I 1 IH-t-t-HII I-12-30 -20 -10 0 10 20 30Ai/e ron deflection, ba = 0.95 ; =
16、140. ,- . -. . -.-. ,. . .-.-. .-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-28 NACA TM NO. 1738 ./l 1 1 tt I 1 I I 1 I m t 1.W I I I I I I I1%1111 (Jyg)ed v -4.3o2 4.3. 0 8.5- i1 1 I 1 I EI12.7 .1 Ino471 rl I I I I II K%ilJTnl.2 -.3-4. .-30 -20
17、-10 0 10 20 30Aileron aefledion, &l deg(b) Hinge-moment coefficient.Figure9.- Continued. . . .- - - - ,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NAiA TN No.1,2.841:4.81738 ,. 291(?-/.2.0.4F3 -.4.8-1.21/ I I J 1I I I I I I I I1A, ,w 1 I I I U I Ii)I ITw.-8+. .-30 -20 _f o 10 20 30 “Aileron defle cfoo, 6U, deq(c) Seal-pressurecoefficient.Figure9.- Continued. . . .- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
