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- W1543453454 abstract "An investigation of the use of low auxiliary horizontal-tail surfaces to alleviate the pitch-up tendency at high lift of an airplane configuration having a T - tail has been conducted in the Langley high-speed 7- by 10-foot tunnel. The basic model had a wing with an aspect ratio of 3, a taper ratio of 0.143, and an unswept 80-percent chord line. The Mach number for most of the tests extended from 0.60 to 0.94 and the angle-of-attack range was from -2 deg. to approximately 24 deg. at the lowest test Mach number. A preliminary study of a systematic series of auxiliary tails indicated that the pitch-up tendency at high lift encountered on the basic model could be greatly alleviated by use of a relatively small, very low-aspect-ratio auxiliary horizontal tail. This tail was located radially with respect to the fuselage center line with 30 deg. negative dihedral and therefore provided a significant favorable increment to directional stability of the model throughout most of the test angle-of-attack range." @default.
- W1543453454 created "2016-06-24" @default.
- W1543453454 creator A5047762320 @default.
- W1543453454 date "1957-12-05" @default.
- W1543453454 modified "2023-09-27" @default.
- W1543453454 title "Investigation at High Subsonic Speeds of the Use of Low Auxiliary Tail Surfaces having Dihedral to Improve the Longitudinal and Directional Stability of a T-Tail Model at High Lift" @default.
- W1543453454 hasPublicationYear "1957" @default.
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