Comparison of the Mach 3.0 aerodynamic characteristics of tension string, tension shell, and 120° conical shapes
James Wayne Sawyer, United States. National Aeronautics and Space Administration, Langley Research Center
National Aeronautics and Space Administration, 1968 - Mathematics - 27 pages
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6-inch model tunnel aerodynamic centers aerodynamic coefficients Aerodynamic Investigation angle of attack axial-force coefficients based on maximum body length CHARACTERISTICS OF TENSION CONICAL SHAPES drag coefficients encountered flow separation Entry Vehicles flow patterns flow turning angle forebody length four tension shell free-stream High-Drag inch absolute 410 International System James Wayne Sawyer Langley 9 Langley Research Center Leeward 1.0 length and nose Mach number maximum diameter NASA TN normal-force coefficients nose cap nose radius number of 3.0 onset of flow pounds per square Reynolds number rmax schlieren photographs Shapes at Mach shown in figure slopes spaced taut strings square inch absolute stagnation pressure string shapes showed susceptible to flow System of Units tension shell shapes tension string models tension string shapes tension string structural tension-string Three decelerates shapes three tension string U.S. Customary Unit values variations in body Windward Leeward 1.0 Windward Leeward 3.0 x 10 Windward zero angle