Computations of the hypersonic flow around sharp cones were carried out using the PNS code with attention given to the heat transfer predictions around the transition region. Results of calculations performed over 5, 8, and 10 deg half-angle sharp cones in the Mach number range of 7 to 10 are presented. It is noted that calculations of this type have become an integral part of the general design procedure for hypersonic vehicles such as the National Aerospace Plane and the Space Shuttle.
Laminar-turbulent transition calculations of heat transfer at hypersonic Mach numbers over sharp cones
ASME Winter Annual Meeting ; 1988 ; Chicago, IL, United States
1988-01-01
Conference paper
No indication
English
Hypersonic laminar-turbulent transition on circular cones and scramjet forebodies
Online Contents | 2004
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