Numerical Analysis of Convective Heating of Two Models of Descent Spacecrafts

Results of numerical simulation of the ideal gas supersonic flow about a descent spacecraft are given. Two models were studied: that of the spacecraft of segmental-conic shape and the Mars Science Laboratory. The analysis is performed of results obtained under various conditions in the oncoming flow for the whole area of the flow: from the bow shock wave to the distant trace. Initial data, used in computations, correspond to conditions of experimental studies in pulsed wind tunnels.