Predictions of a Supersonic Jet-in-Crossflow: Comparisons Among CFD Solvers and with Experiment
Final rept. Jan 2011-May 2014
ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD WEAPONS AND MATERIALS RESEARCH DIRECTORATE
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A supersonic jet interaction flowfield with pressure ratios of 2.8-16.7 exhausting into subsonic and transonic crossflows Mach 0.5-0.8 was simulated using computational fluid dynamics and compared to experimental particle image velocimetry data. Three independent studies using different Reynolds-averaged Navier-Stokes flow solvers and a variety of turbulence models were used to assess the accuracy level of the predicted downstream flow physics of the jet interaction problem. Evaluation of the prediction of the downstream flow structure was made via comparisons of the three components of velocity and turbulent kinetic energy. In general, the predicted jet interaction flowfield was highly sensitive to the turbulence model used, with performance of the turbulence model being dependent on the flow solver, and relatively insensitive to crossflow Mach number in the range investigated.
- Fluid Mechanics