Effects of horizontal-tail position and a wing leading-edge modification consisting of a full-span flap and a partial-span chord-extension on the aerodynamic characteristics in pitch at high subsonic speeds of a model with a 45 degree sweptback wing

Author / Creator

Morrison, William D. author

Available as

Online

Summary

An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of varying the horizontal-tail position relative to the wing chord plane on the aerodynamic ch...

An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of varying the horizontal-tail position relative to the wing chord plane on the aerodynamic characteristics in pitch of a general research model having a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.30, and NACA 65A006 airfoil sections. The investigation also included the effects of a wing modification consisting of a full-span leading-edge flap deflected 6 degrees and an outboard partial-span chord-extension. The test Mach numbers ranged from 0.40 to 0.93 and the corresponding Reynolds numbers ranged frcm about 2,000,000 to 3,000,000.

In the range of horizontal-tail positions investigated, the most desirable pitching-moment characteristics obtained, either with or without the wing modification, were with the lowest tail position (0.139 semispan below wing chord plane extended). The wing modification provided considerable improvement in pitching-moment characteristics for tail positions above the chord plane extended. The improvements obtained at Mach numbers near 0.90 were much smaller, however, than those obtained at lower Mach numbers.

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