1、e F TEcrnICAL MEMORANDUM x-35 EFFETS OF VERTICALTAIL SIZE AND A VENTRAL FIN ON TEE STATIC LATHiAL AM) DIRZCTIONAL STABILITY DERIVATIVES By Walter B. Olstad An investigation was made of the effects of vertical-tail size and a ventral fin on the static lateral and directional stability derivatives of
2、a 0.048-scale model of a horizontal-attitude vertical-take-off-ad- ianding (VTOL) airplane. to 1.2, with angles of attack up to 25 and angles of sideslip of Oo, -3.250, and -6.50. The model was tested at Mach numbers from 0.6 The results indicated that the addition of the small vertical tail resulte
3、d in a directionally s%able configuration for angles of attack up to at least llo. Use of a vertical tail with a 33-percent greater exposed area increased the directional-stability contribution of the vertical tail by approximately 15 to 20 percent throughout most of the Mach number range. the confi
4、guration with the large vertical tail. tral fin to the configuration produced no noticeable change in the lateral and directional derivatives. directional-stability contribution of the horizontal tail was generally from 39 to 49 percent of the stability contribution of the small verti- cal tail. inc
5、reasing angle of attack. The -30 dihedral angle of the horizontal tail produced a large negative increment in the effective dihedral. A rapid increase in pitching-moment coefficient with increasing angle of sideslip was produced by the combined effects of horizontal-tail nega- tive dihedral, high wi
6、ng position, and low horizontal-tail position. The effective dihedral was generally positive for The addition of a ven- At an angle of attack of Oo, the This directional-stability contribution decreased with n Provided by IHSNot for ResaleNo reproduction or networking permitted without license from
7、IHS-,-,-2 An investigation has been conducted at transonic speeds in the Langley 8-foot transonic pressure tunnel to determine the effects of horizontal-tail negative dihedral, vertical-tail size, and ventral fins on the aerodynamic characteristics of a horizontal-attitude vertical- take-off-and-lan
8、ding (VTOL) airplane. numbers ranging from 0.6 to 1.2 and angles of attack up to 25. longitudinal-stability characteristics, including the effects of horizontal-tail negative-dihedral angle, were reported in reference 1. This previous study indicated that the horizontal tail with a dihedral angle of
9、 -30 yielded the most desirable longitudinal-stability results. Therefore, this horizontal tail was chosen for the lateral-stability investigation. including the effects of vertical-tail size and a ventral fin, are reported herein. The average test Reynolds number based on the mean 6 6 aerodynamic c
10、hord varied from 1.42 x 10 to 1.90 x 10 over the Mach number range. This model was tested at Mach The The results of the lateral-stability investigation, b wing span, in. d drag coefficient, F;/qS cD, i CL lift coefficient, FL/qS c2 rolling-moment coefficient, Mx/qSb Internal drag (2s internal drag
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