Turbulence modeling of 3D high-speed flows with upstream-informed corrections

Turbulence modeling has the potential to revolutionize high-speed vehicle design by serving as a co-equal partner costly and challenging ground flight testing. However, fundamental assumptions that make turbulence such an appealing alternative its scale-resolved counterparts also degrade accuracy for practical configurations, especially when fully 3D flows are considered. The current investigation develops methodology improve performance of complex Mach 8.3, shock boundary layer interaction (SBLI) in double fin geometry. A representative two-equation model, with low-Reynolds number terms, is used test-bed. Deficiencies baseline model first elucidated using benchmark test cases involving Mach~11.1 zero pressure gradient Mach~6.17 flow over axisymmetric compression corner. From among different possibilities, two coefficients introduced inhibit non-physical over-amplification (i) production (ii) length-scale downstream wave. rely on terms already present original which simplifies implementation maintains computational costs. values predicated distribution quantities upstream shock; this ensures modifications do not predictions simpler situations attached layers, where they unnecessary. effects shown result significant improvements surface wall heat flux SBLI case, contains numerous features observed 2D situations, separation, skewed layers centerline vortices. Considerations inflow variables mesh resolution provided.