AEROTHERMODYNAMICS OF THE STARDUST SAMPLE RETURN CAPSULE

The development of a new high-Ž delity methodology for predicting entry  ows with coupled radiation and ablation is described. The prediction methodology consists of an axisymmetric, nonequilibrium, Navier–Stokes  ow solver loosely coupled to a radiation prediction code and a material thermal response code. The methodology is used to simulate the 12.6-km/s Earth atmospheric entry of the Stardust sample return capsule using ablating and nonablating boundary conditions. These  ow simulations are used to size and design the Stardust forebody and afterbody heatshields and develop arcjet test conditions and models. The  ow simulations indicate that the afterbody heating and pressure proŽ les in time are signiŽ cantly different than the forebody heating and pressure proŽ les. This result is explained in terms of the pertinent aerothermodynamicsof the  owŽ eld and the vehicle’s geometry.When applied to the afterbody thermal protection system, these results show that the traditional afterbody heatshield design approach is nonconservative for the Stardust sample return capsule shape and entry conditions.

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