Calculation of stagnation-point heating rates associated with Stardust vehicle

Stagnation-point heating rate is calculated for the Stardust entry vehicle and for its heat-shield models tested in an arcjet wind tunnel. The calculations are made for the convective component for both the laminar and turbulent cases, the radiative component produced by the gas flow, and the radiative component produced by solid particles. A one-dimensional viscous shock, layer method is used with an up-to-date thermochernical, gas-surface interaction, radiation, turbulence, and particulate models. For the flighteases, radiation absorption in the boundary layer is found to increase the convective heating rate by a factor of up to two. The calculated sums of all heating rates for the flight cases are nearly the same as those obtained by Olynick et al., and are substantially larger than those by Gupta. The calculated sums of all heating rates for the arcjet test cases are smaller than those calculated by the formula of Fay and Riddell, and are nearly the same as those experimentally determined using copper calorimeters.