Minsul LEE, Kyu Hong KIM, Hyoungjin KIM

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST 2024-0046

In this study, Multi-objective shape optimization of the re-entry capsule was conducted by using aero-thermal analysis engineering code. Capsule geometry was defined based on three-dimensional axisymmetric Viking geometry having five design parameters. Automatic surface meshing was carried out using a script that creates a p3d format and converts it to unstructured triangular surface mesh. Aero-thermal analysis was carried out using an engineering code that uses the local surface inclination method to estimate inviscid pressure and reference temperature method to calculate the skin friction coefficient. A streamline tracing method was implemented to calculate the local Reynolds number. Stagnation heat flux was estimated using the Brandis formula. Re-entry capsule geometry was optimized in the flow condition of Mach 20, angle of attack 20 deg, and altitude 57km using a multi-objective evolutionary algorithm. The optimum solution was selected considering the maximum lift-drag ratio, volumetric efficiency, and minimum stagnation heat flux.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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