Missile Interceptor Base Flow Simulation

The Phase II program concentrates on improving computational capabilities for analyzing hypersonic missile base flow configurations by utilizing state-of-the-art experimental data and complementary LES data to support development and validation of RANS turbulence models for propulsive base flows. Previously, CRAFT Tech has extended turbulence modeling capabilities for cold propulsive base flows utilizing high-fidelity experimental data from University of Mississippi’s National Center for Physical Acoustics and accompanying LES. The current Phase II program will involve performing LES to provide valuable mean and fluctuating flow field data complementing NCPA hot base flow experimental data at various flight conditions. This extended data base will facilitate validation of CRAFT Tech’s high-speed turbulence modeling capability for hot propulsive base flows. Advanced turbulence modeling features such as scalar fluctuation modeling, compressibility and baroclinic torque corrections, and relizable k-e; extensions will be incorporated in an adaptive strategy to provide a unified turbulence model suited for application over the missile body, base region, and plume. The turbulence model development and validation resulting from this program will produce a more cost effective design/anlaysis process by improving confidence in future CFD analysis of missile base flows and providing more accurate prediction of missile base drag and plume aero-thermal effects.