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Heating Effect On Blunt Re-Entry Capsule
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1 Geometry 0 Meshes 0 Simulation setups 0 ResultsAbout this project
This project simulates hypersonic flow over a blunt re-entry capsule to visualize aerodynamic heating phenomena. A 2D axisymmetric geometry was modeled consisting of a hemispherical nose and a short conical shoulder. The simulation uses a steady-state compressible RANS solver (k-ω SST turbulence model) with ideal-gas air at Mach 7 and freestream temperature of 220 K. The objective is to analyze the formation of the bow shock, the resulting rise in static temperature at the stagnation region, and the wall heat-flux distribution. Contour plots of pressure, temperature, and heat flux clearly demonstrate that the stagnation point experiences maximum heating, validating the expected aerodynamic heating behavior for blunt bodies during atmospheric re-entry.
