configurations will experience large heat loads. Accurateprediction of these complex flow fields is necessary for designing appropriate heatshields. Thermal-chemical nonequilibrium, nonequilibrium radiation, and surface-ablation effects will be important under these conditions. This project will develop and demonstrate a new space-marching Navier-Stokes scheme that will be computationally fast and efficient and will also be able to address these flow-field effects. Phase I will focus on axisymmetric perfect-gas flow over a typical AOTV forebody, and will use a space-marching approach with Van Leer flux splitting. The project will demonstrate this new umerical capability by predicting hypersonic flow over a 70-degree phere-cone under typical AOTV conditions, and provide a detailed engineering report. Phase II will address the extensions to include three-dimensional flows, a wide range of nonequilibrium-to-equilibrium flows, radiation and surface-ablation effects, and will include near- as well as far-wake flow field regions. The developed code(s), user's manual(s), and a final engineering report will be provided at the end of Phase II.Commercial applications include the design and analysis of various hypersonic penetration aids and decoys, NASP, TAVs, AOTVs and aerobrakes, and AFE configurations. In the absence of sufficient flight data, these computational fluid dynamics capabilities will help generate the data base for such advanced design concepts.space marching, Navier-Stokes, aerobrake, nonequilibrium, ablation, radiationSTATUS: Phase I Only
