Method of integral relations is used to determine equilibrium air properties in subsonic and transonic portions of flowfield about body entering earth's atmosphere at hypersonic velocities and zero angle of attack; by interpolating certain quantities as linear functions between body and shock, equations of motion can be integrated across shock layer and replaced by set of ordinary differential equations that are solved by direct numerical integration along body; numerical results for small-scale Apollo vehicle at altitude of 171,111 ft and velocity of 34,582 fps are presented.
Symmetrical, equilibrium flow past blunt body at superorbital re-entry speeds
AIAA J
AIAA Journal ; 5 , n 4
1967
8 pages
Article (Journal)
English
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Aerothermodynamics Behind a Blunt Body at Superorbital Speeds
Online Contents | 2010
|Variable-lift re-entry at superorbital and orbital speeds
Engineering Index Backfile | 1963
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