Heat-transfer distribution data obtained on 9° half-angle cone at Mach numbers near 20 and freestream Reynolds number between 8000 and 15,000/in. in hypervelocity tunnels are presented; test data are compared with L.Lees'laminar heat-transfer theory and shock-tunnel data on similar cones; good agreement between theory and data is obtained; experimental pressure and heat-transfer distributions were correlated over wide range of nose-bluntness ratios, cone half-angles, and Mach numbers by modifying correlation parameters proposed by H.K.Cheng.
Laminar heat transfer to spherically blunted cones at hypersonic conditions
AIAA J
AIAA Journal ; 2 , n 3
1964
7 pages
Article (Journal)
English
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