Surface pressures were measured on plates with various values of angle of attack and of leading-edge sweep for Mach numbers of 4 and 5.7 and correlated for wide range of variables by method developed from boundary layer and blast-wave theory; method to predict variation in local Reynolds number with leading-edge sweep; applicability to trajectory of hypersonic winged vehicle in upper reaches of atmosphere.
Effect of leading-edge sweep and surface inclination on hypersonic flow field over blunt flat plate
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 12-26-58A
1959
45 pages
Report
English
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Blunt-leading-edge problem in hypersonic flow
Engineering Index Backfile | 1963
|THE BLUNT-LEADING-EDGE PROBLEM IN HYPERSONIC FLOW
AIAA | 1963
|