High-Resolution Modeling of Plume Exhaust Shock-Boundary Layer Interactions

A thruster jet emerging laterally from a missile surface into a hypersonic external crossflow produces a complex environment which poses a significant effect on the vehicle control. A good understanding of the phenomenon can be achieved only with highly accurate physics computations. Our innovation offers to greatly enhance prediction qualities in a high-performance framework. This effort will be devoted on establishing the key elements of our model and simulation techniques in describing the underlying physics with both precision and computational efficiency. Phase I will address the effect of various physical processes, with the end product delivering a software for large-scale applications with fidelity and speed.Once implemented and benchmarked, we anticipate that our innovation will offer an exceptionally improved, user-friendly technology with a high readiness level for full-scale analysis of interceptor maneuverability. Approved for Public Release | 22-MDA-11339 (13 Dec 22)