1、j! c c 6 _- - - e*/ RM L51ToB RESEARCH MEMORANDUM EFFECT OF VERTICAL LOCATION OF A HORIZONTAL TAIL ON THE STATIC ONGTUDINAL STABILITY CHARACTERISTICS OF BACK-WING - FUSE LAGE COMBINATION OF ASPECT RATIO 8 AT A REYNOLDS NUMBER OF 4.0 x lo6 y Rein0 J. Salrni and William A. Jacques Langley Aeronautic L
2、angley Fie ATIO! r“.NCEtLE b- :)“ A that is, the tail effectiveness through the high lift-coefficient range increased when the tail wae located just below the extended wing-chord plane, but 88 the tail height above the wing-chord plane was increased, the tail effectiveness decreased through the high
3、 lift-coefficient range. At the highest position teeted, the tailwaa destabilizing in the high lift-coefficient range. AB a result of large improvements in the stabil- ity in the high lift-coefficient range obtained with leading-edge. flaps * whereas .for a tail height of 0.30Ob/2, .a/ 1951. 4. Fost
4、er, Gerald V., and Griner, Roland F.: A Study of Several Factors Affecting the Stability Contributed by a Horizontal Tail at Various Vertical Position8 on a Sweptback-Wing Airplane Model. NACA RM L9rn9, 1949. 5. Sivells, James C., and Salmi, Rachel M.: Jet-Boundary Corrections for Complete and Semis
5、pan Swept Wings in Closed Circular Wind Tunnels. NACA TN 2454, 1951. 6. Kayten, Gerald G.: Analysis of Wind-Tunnel Stability and Control Tests in Terms of Flying Qualities of Full-scale Airplanes. NACA Rep. 825, 1945. (Formerw RACA ARR 3522. ) - I . :I -. Provided by IHSNot for ResaleNo reproduction
6、 or networking permitted without license from IHS-,-,-NACA RM L51J08 “ Mean aerodynamic chord, 16.672 I wino I Tu;/- I Aspect ratio 8.0 4.0 Toper rafio . 0.45 0.45 IArea. su ff 1 14.02 I 2.249 I L “- Figure 1.- Geometry of 45 sweptback wing of .aspect ratio 8, fuselage and tail. All dfmensions are i
7、n inches except where noted. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . 0.6b, normal to ohord line .-t300 0.38 dinr, 5.60 rad. Figure 2.- Typlcal sections of high-lift and stall-control devicee parallel to the plane of symmetry excep
8、t where noted. wnsione are in Inches except where noted. 1 . “ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . I . . I * , 3 I I (a) Front view. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.
9、 . . . . . . . . “. (b) Rear viev. Figure 3.- Concluded. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I Tail kight,percont b/2 . ohve wing-chord plane e:+- - 14.Q .“ “ 4.5 - jt“a- Paint of rotqtion of wing-cllord plone Wing-chord plane ce P o P
10、. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . . . . . . - . Phil3 .inp z mll off A Figure 5.- Effect of a horizontal tail at variok vertical locationa on thepitching-moment characterietice for various flap conflgura- tione and t
11、wo incidence wing angles on a 45 eweptback wing of aepect ratio 8.0. All tail-incidence angles are approximately -4. I I 1. . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.8 .6 .4 .2 0 -. 2 -4 8 /2 /6 20 24 28 E, deg Figure 6.- Variation of lift
12、 coefficient with angle of attack of the 45 sveptback tail of aspect ratio 4.0 and UCA 631A012 alrfoil ,gectioQe. R 2.26 X lo6 correeponding to the KLW R 4-00 X 10 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 - NACA RM L5lJO8 120 .a0 .40 0 -4
13、0 320 .a0 0 . -140 1.60 120 .80 (a) Plain wing. Figure 7.- Variation with lift coefficient of dCm/dCL for the wing- fuselage combination and dCm/dCL- for Cm = 0 for the tail-on configurations. Center of gravity at 0.25E. ! t “ . I ! - I . .-, I Provided by IHSNot for ResaleNo reproduction or network
14、ing permitted without license from IHS-,-,-NACA M- L5lJO8 120 -80 0 120 .& m -80 0 740 320 .80 0 -40 320 0 (b) 0.573/2 and 0.800b/2 fences. Figure 7. - Continued. I I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 I I I 0 .8 1: -2 CL 1.6 0 740 0
15、.8 1.2 1.6 CL I ( c) 0.4/2 leading-edge flaps and 0.475b/2 and 0.800b/2 fences. “ Figure 7.- Continued. I I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-KO .eo - 0- 740 0 3. -320 0 -I20 120 .80 0 740 .%80 -120 0 .4 .a . 1.2 1.6 0 .4- .a 1.2 . 1.6
16、CL CL -& = 40 “-“&=ao v (a) 0.3!%/2 split flape, 0.45b/2 leading-edge flaps and 0.575b/2 and 0.80.0b/2 fences. Figure 7.- Continued. . I i Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 0 NACA Rh! L5lJ08 0 .4 .8 1.2 1.6 0 .4 .8 1.2 1.6 CL OL (e)
17、0.35b/2 split flaps and- 0.45b/2 leading- edge flaps. Figure 7.- Continued. . ! Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-a0 -X20 -i 0 .4 .a 1.2 1.6 0 .4 .0 . 1.2 1.6 cL CL 5r = 4“ “_ 1, = oo (f) .0.50b/2 extended split flap8, 0.4%/2 leadfng- e
18、dge flaps, and 0.575b/2 and O.&b/2 fences. Figure 7.- Concluded. I I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I 8 16 24 16 0 0 t ,O ,O 0 z -1 .o 1 .o 0 “ z -1 .o 16 8 0 16 8 0 0 z -1 .o Figure 8.- Variation of tail effectiveness parameter T an
19、d the effective dmwaeh angle e with angle of attack. 0 z .1.0 I I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I NACA FtM L51J08 “L 8 8, dog 0 0 0 T c -1.0 -8 -1.0 I 16 16 8 0 0 c -1.0 I I 24 16 “- E, z I .O 0 z -1.0 (b) 0.573/2 and 0.800b/2 fences. Figure 8.- Continued. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
