Determination of Aerodynamic Heating of Hypersonic Glider Wings

摘要

A simplified, approximate engineering method is developed, in order to predict the surface heat transfer on a flat plate with pressure gradient, caused by nose bluntness and viscous interaction effects. This method also attempts to allow for the effect of sweep and angle of attack on the surface heat transfer. Good agreement is obtained when correlating the new method with a limited amount of experimental data except, at conditions where the pressure gradient approaches zero. These experimental studies are for large Mach number, low density, real gas flow. (Author)