Results of investigations of flow in wake of hypersonic vehicles; nonsimilar solutions of equations governing "far wake" are obtained, and numerical results for flow field in wake of ballistic range and wind-tunnel models and of flight-size vehicle; ballistic range experiments with conical models of 10°, 15°, and 27 1/2 ° semivertex angles are described; model velocity ranges between 4000 and 17,000 fps with range pressures varying from 15 to 330 mm of Hg in air; analysis is used to compute and correlate transition parameters; predictions of location of transition in wake of 12° semivertex angle cone at 22,000 fps are made for altitude range from 200,000 to 100,000 ft.
Hypersonic laminar wakes and transition studies
AIAA J
AIAA Journal ; 2 , n 5
1964
9 pages
Aufsatz (Zeitschrift)
Englisch
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