1、RESEARCH MEMORANDUM MODEL HAVING A 42.8 SIWPTBACK ClRC%LAR=ARC WING WIT. ASPECT RATIO 4.00, TAPER RATIO 0.50, Kenneth W. Goodson and Paul COMS tlty .Lo“- NATIONAL ADVISORY C FOR AERONAUTICS Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by
2、IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 The afleron effectiveneaa decreaebd with increase- in angle of attack for down aileron deflecttons-but remained nearly constant for up deflections The accelerated development of jet-propelled aircraft durlng tror
3、ld ar II resulted m-the creation of motors (turbojet, ram jet, and rocket) capable of propelling airplanes at suersanic epeoda Airplanes that are to fly throu1 .swe-ptback wing having an aapect ratio of 2.w and a taper ratio of 0.42. The “lng had an NACA 65-110 airfoil section. The reeults of the te
4、sts are presented positive when trailing edge aom rudder deflection moanurea in plane parallel to fuselage center line, degrees 1. split-flap deflection measured in glens gerpenecular to reference =ne, degrees pla-in flap d.eflection measwad in plene perpendicular to wing reference line, degreee ang
5、le of ewee3back measured to leadfng edge; degrees - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-5 . x MO free-stream Mach number . Subscript: the number prscedhg the first dmh (42.8) give8 e sweepback A in degrees measured wfth rewect to the lead
6、fng edge, the number f ollowlsy: the first Oaeh (4 -00) gives the aspect ratio A, and the nuniber following the second- dash (0.50) gives the kper ratio .X Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-in figure I( a) . The cfrcuhr-an, aspect ratio
7、 4, wing was comtructed of mahogany and was fitted with 20-percent-chord split flaps and Wpth 15-percent-chord nose flaps (moasured perpendicular to the wing reference line). The split flapEc and tho nose flaps are shown deflected in figure 4. The split-flap deflection angle was measured betweon the
8、 lower contour of the wing and the flap surface, and the nom-flap deflection ml measured with respect to the chord lines of the and the nose flap (See section A-A of fig . le) A drawing of a 810% in tho wiq baaing edge is shown in figwe 5 . me lwge fuselage was Fitted a flat-top dorsal was tested in
9、 the low position. shown in the three*view Bra- of figure l(b) The wing of the small fuselage had a 20-percent-chord plain flap and aileron (measured perpendicular to tho wug reference line) . The slain flap and the aileran deflection angles were measured between tho wing chord.llne and the respecti
10、ve flap or aileron chord line (fig . l(b) ) The mall fuaelage had a vertical tail (amall) of the * sm plan form .aa the large fuselage but used an NACA 27-010 - -foil section Ineteab of the thn eteel Zlato. Tke model was also tested with a large vortical tail (fig l(b) having a 40 -3 - 1.35 - 0.35 p
11、lan row. me large verttca tail coneisted of an NACA 27-010 airfoil section at the root and. an NACA 27-OCfl airfoil section at the tip. The horizontal tail was the same a8 for the large fuselage a Several dorsal and yentral fairing configurations, shown in figwe 9, vere tested with the large and the
12、 mall vertical taile. The lower vertical tail is shown in figwe 9 A draw5ng shorn the wing stall-control vane or fence used on the model is ahom in figlire 10. The selection of this vane vas determined by tests of reference 1. In order to facili- tate the installation of the horizontal tail in the r
13、aised positions (fig . 11) , a coefficients were corrected for blocking by the method of reference 4. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8 The data have been corrected for tho horizontal buoyancy cause . , . 18 Low wing with amall fusela
14、ge (I = 3 .Oo), amall vertical tail: Effect of dorsal and ventral fairtngs on 4310 aerodpamic characteristics in yaw .-. 19 Lateral-stabllity derivativee 20 Aerodynamic characteristics in yaw 21 Low wing vith mall fuselage (I = 3 .OO) large vertical tail: Xffect of doyea3 fairings on the asrodyrsRlr
15、ric characterzatics inyaw .,22 - Laterall-coatrol vanes on lateral stabilitr was negligible. “ -l Tbe aileron effectivenoes (fig. 27) decreaaee with crease in angle of attack for positive aileron deflections but remains nearly constant for negative deflections e The effect of the stall- control vane
16、s on the aileron characterietfcR was negligible. Rudder-control and hinge-moment characteristics are presented fn figure 28. The rudder effectiveness ed for I tihe *decrsam in effective 63hedP.al .cawed by lowwing the whg. The tail .contribution to the effective dihedral was greater for the IOIT vin
17、g than for the amhi Ofn = 0; thin steel vertical tail. Turbulence net in tunnel. . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-t Y Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I # F c Mgure
18、 4.- Split flaps and nose flap deflected on a model with a 42.8 -4.00 - 0.50 wing. = 550: Ofr = 300. . . . . . . . . . . . . . . . . . E Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permit
19、ted without license from IHS-,-,-I , a . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-f Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,. . . . . . 1. Figure 6.- A photograph of whg fillets tested
20、 on a model with a 42.8 -4.00 - 0.50 wing. . . . . . . . . . . . . . . . E Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . I L Figure 7. - Photograp
21、h of the small fuselage model with a 42.8 -4.00 - 0.50 wing mounted in the Langley 300 MPH 7- by 10-foot tunnel. 8 = 00; 6 = 00. fP fn rs -3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . I . Figure 8.- Photograph of the small fuselage model with a 42.8 -4.00 -0.50 wing mounted Ln the Langley 300 MPH 7- by l0-foot tunnel. 6 = 00; gf = . fP n . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
