Investigation of Supersonic and Hypersonic Missile Interceptor Base Flows Using an Advanced Computational Framework

A computational investigation of missile interceptor base flows in a supersonic/hypersonic application is proposed. High-fidelity three-dimensional simulations will be conducted using the proprietary framework Rocstar. The computational framework includes a compressible flow solver with advanced LES turbulence models and has flexibility sufficient to investigate a variety of base flow configurations under widely varying conditions. As a feasibility study for Rocstar, in Phase I we propose validated simulations for the flow past the cylindrical blunt afterbody configuration of Herrin and Dutton (1994) at Mach number of 2.5. In the Option period, we will develop a validation matrix, including a variety of geometries, for implementation during Phase II. We will also execute a simulation of the boat-tailed geometry. Professor J. Craig Dutton will serve as technical advisor to IllinoisRocstar on the SBIR project. The overall goal of this work is to develop, validate, and commercialize a numerical tool suitable for design and analysis. The code should accurately predict supersonic and hypersonic base flow characteristics to within ±5%, especially pressure and velocity data. At the conclusion of Phase I and the Option, we will have completed a study assessing Rocstar capabilities, compared two well-known afterbody geometries, and assembled a set of validation cases to direct and extend Rocstar for turbulent base flow.