HYPERSONIC MODEL TESTING IN A SHOCK TUNNEL

A shock tunnel is used to perform tests at hypersonic flow conditions including weak real gas effects. Pressure and heat nux distributions a re measured around typical re-entry configurations. From these data c( p) values and Stanton numbers are deduced. For constant Mach and Reyno lds number the experimental results achieved indicate a strong influen ce of the total temperature on the Stanton number distribution. For th e results presented this behavior is mainly based on entropy layer and viscous interaction effects. A correlation function which takes into account these effects correlates the Stanton numbers achieved for diff erent now conditions and in different wind tunnels fairly well.