An Investigation of HYFLEX Flight Data For Empirical Hypersonic Heating Prediction

摘要

An investigation was made for the HYFLEX windward heat flux data to obtain a correlation of windward heat transfer with free stream and nose stagnation conditions. To evaluate nose bluntness and viscous interaction effects, a correlation using a reduced Stanton number was attempted. The reduced Stanton number St_(Miller) was modified to evaluate angle of attack effect on the measured heat flux. Then, dependency of the modified Stanton number on several common flow parameters was examined. Clear dependency on the enthalpy difference between total and wall enthalpy became evident in the examination showing dominant effect of flow condition behind nose normal shock on the windward heating rate. From these examination study a good correlation curve was obtained which shows clear dependency of the heat flux on the density ratio across the nose normal shock in both real gas and perfect gas flight region where temperature behind the normal shock is above and below 2140°C, respectively. This correlation result is extremely useful as a reference data for a flight aerodynamics heating prediction from ground data to flight extrapolation.