Heat Flux Computation in Hypersonic Flow with Cartesian Mesh Using Hybrid Solution Methodology
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A hybrid solution methodology has been developed to solve laminar hypersonic flow by starting the solution with a Cartesian mesh Euler solution and then resolving the boundary layer by building prism layers from the wall panels obtained from the Cartesian mesh and performing laminar Navier-Stokes computation for this prism layer after mapping the Cartesian mesh Euler solution on to this prism layer. The solver, developed based on this approach when compared with recent experimental data, predicts the heat flux with good accuracy for a laminar hypersonic flow over typical sphere cone cylinder flare geometry. Since the whole procedure is fully automated, it has a good potential to handle near-wall resolution with a Cartesian mesh for complex geometries as well.
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