Experimental Investigation Of Pressure Distribution And Static Aerodynamic Characteristics For Three Supersonic Impact Ballistic Reentry Shapes At Mach Numbers Of 193 255 And 305

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Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Numbers of 1.93, 2.55, and 3.05

Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Numbers of 1.93, 2.55, and 3.05

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Total Pages	: 44
Release	: 1961
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Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Numbers of 1.93, 2.55, and 3.05

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