Effect of Nose Geometry on the Aerothermodynamic Environment of Shuttle Entry Configurations
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[1] R. K. Matthews,et al. Space shuttle: Heat transfer rate measurements of North American Rockwell orbiter (161B) at nominal Mach number of 8 , 1971 .
[2] K. Wang,et al. Separation Patterns of Boundary Layer over an Inclined Body of Revolution , 1971 .
[3] J. N. Hefner. Lee-surface heating and flow phenomena on space shuttle orbiters at large angles of attack and hypersonic speeds , 1972 .
[4] P. E. Everhart,et al. An experimental study of the pressure and heat-transfer distribution on a 70 deg sweep slab delta wing in hypersonic flow , 1963 .
[5] J. Der,et al. A Study of General Three-Dimensional Boundary-Layer Problems by an Exact Numerical Method , 1969 .
[6] D. Reda,et al. Hypersonic transitional and turbulent flow studies on a lifting entry vehicle , 1972 .
[7] F. R. Riddell,et al. Theory of Stagnation Point Heat Transfer in Dissociated Air , 1958 .
[8] John C. Adams,et al. Hypersonic Lifting Body Windward Surface Flow-Field Analysis for High Angles of Incidence , 1973 .