Transition characteristics were determined for smooth, blunt nosed cones varying from 27 to 60° in included angle; Mach number effects were small for small bluntnesses but increased for larger; strongest effect was in Mach number range 1.61 to 1.82; increase in nose bluntness caused decrease in transition distance and transition Reynolds number.
Effects of cone angle, Mach number, and nose blunting on transition at supersonic speeds
NASA -- Tech Note
1961
31 pages
Article (Journal)
English
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Laminar turbulent transition at hypersonic speeds: the effects of nose blunting
British Library Conference Proceedings | 1995
|Laminar turbulent transition at hypersonic speeds: the effects of nose blunting
British Library Online Contents | 1995
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