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- W332580532 abstract "Hypersonic stability, control, and performance characteristics were determined on a single-stage-to-orbit vehicle based on control-configured stability concepts. The configuration (0.006-scale model) had a large body with a small 50 deg swept wing. Two vertical-fin arrangements were investigated which consisted of a large center-line vertical tail and small wing-tip fins. The wing-tip fins had movable surfaces called controllers which could be deflected outward. Longitudinal and lateral directional characteristics were obtained over an angle-of-attack rage from 0 deg to 40 deg. The effects of tip-fin controller deflection on roll- and yaw-control characteristics at a sideslip angle of 0 deg were obtained. This investigation was conducted in the Langley 20 Inch Mach 6 Tunnel." @default.
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- W332580532 date "1983-01-01" @default.
- W332580532 modified "2023-09-24" @default.
- W332580532 title "Effect of modifications of aerodynamic characteristics of a single-stage-to-orbit vehicle at Mach 5.9" @default.
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