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• W2004564505 abstract "Several conceptual hypersonic research airplanes, designed within the constraints of a B-52 launch aircraft, have been studied experimentally and analytically at Mach numbers from 0.2 to 6.0. Vehicles built to these criteria for Mach 6 cruise were shown to be feasible, if careful attention was paid to the low speed lift, drag, and high angle of attack stability to assure successful landings and transonic pitch angle maneuvers. The integrated scramjet engine drag was high at subsonic speeds and appears to be constant with Reynolds number. The variable geometry airfoil used previously to improve directional stability was shown to be equally adaptable to the improvement of longitudinal stability. The vortex lattice theory gave good subsonic predictions of lift, drag due to lift, and pitching moments. Wind tunnel tests must be relied on for the drag at zero lift, trim, static margins and lateral-directional stability. The Gentry Hypersonic Arbitrary Body Program gave good predictions of the trends of lift, drag, and pitching moments with angle of attack at Mach numbers above 3, but the level of the values were not consistently predicted. No currently available theory or program gave accurate predictions of directional stability or dihedral effects at hypersonic speeds." @default.
• W2004564505 created "2016-06-24" @default.
• W2004564505 creator A5031716901 @default.
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• W2004564505 date "1978-11-01" @default.
• W2004564505 modified "2023-09-24" @default.
• W2004564505 title "An Aerodynamic Analysis of Several Hypersonic Research Airplane Concepts from M= 0.2 to 6.0" @default.
• W2004564505 cites W1972240134 @default.
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• W2004564505 doi "https://doi.org/10.2514/3.58437" @default.
• W2004564505 hasPublicationYear "1978" @default.
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