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Comparison of the minimum drag of two versions of a modified delta-wing fighter as obtained from flight tests of rocket-boosted models and equivalent bodies between Mach numbers of 0.80 and 1.64

Description: Report presenting an investigation to determine the reduction in minimum drag that could be obtained at supersonic speeds by redesigning the fuselage and reducing the wing and tail thickness of a modified delta-wing fighter-type airplane. Results regarding the mass-flow ratio, total-pressure recovery, and drag are provided.
Date: September 24, 1956
Creator: Hasting, Earl C., Jr. & Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department