A first principles based modeling approach utilizing fluid structure interaction is proposed to enable simulation of transient combustion effects on the observable signatures of maneuvering hypersonic configurations during extreme maneuvers. Existing 3D computational fluid dynamics (CFD) and computational structural dynamics (CSD) software previously used to simulate and design rocket engines including turbulence (RANS, DES, and LES), combustion, ignition, particles, and smoke phenomena is described. Changes to the software to enable simulation of extreme maneuvers are proposed. Plans to integrate the software and models into the current DoD plume flowfield tools are discussed.
