EXPERIMENTAL INVESTIGATION OF THE MEAN FLOW AND STABILITY OF THE LAMINAR SUPERSONIC CONE WAKE.
MASSACHUSETTS INST OF TECH CAMBRIDGE DEPT OF AERONAUTICS AND ASTRONAUTICS
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The mean flow and stability of the near wake of a cone at Mach number 4.3 were studied experimentally. Free stream Reynolds numbers varied from 40,600 to 94,300. The cone had a 7 degree half angle, a sharp nose, and a wall temperature very close to recovery temperature. Important differences between the measured supersonic wake and other investigators measurements in hypersonic cone wakes are found. Author
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