Effect of Unsymmetrical Nose-Bluntness of the Pressure Distribution over a 10 Degree Cone at Mach-14.
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
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The pressure distribution over a 10 deg cone was measured in ARLs 20-inch hypersonic wind tunnel at Mach-14 and for various angles of attack and sideslip. The effect of different unsymmetrically blunted noses, with small bluntness ratios, on the pressure distribution is investigated. Test results relate any small unsymmetrical nose bluntness to the rotational symmetry of the flow over a body of revolution at high Mach numbers. The reported test complement, AD-711 921. Author
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