Abstract
A multi-physics frame work has been setup for the simulation of surface heat flux for nonablating hypersonic reentry vehicles and presented in this paper. The main goal of this work was to set up a simple approach for the heat flux prediction during the reentry of the vehicle. The vehicle considered in the calculation is an axisymmetric vehicle flying at zero degree angle of attack. Chemical nonequilibrium in the flowfield is simulated by implementing a set of finite rate equations in the laminar finite rate model in FLUENT. The frame work set up was validated with the results available in the literature. Good correlation was observed between the results from the commercial code with the implemented equations and the results from the literature.
Highlights
The hypersonic reentry vehicle is immersed in a hot gas as the kinetic energy of the flow is dissipated by viscous effects
It was identified that aero thermal heat flux prediction and material thermal response is evaluated using in house codes like SACCARA (Sandia Advanced Code for Compressible Aerothermodynamics Research and Analysis) [2], GIANTS (Gauss-Siedel Implicit Aerothermodynamic Navier-Stokes code with thermo chemical surface conditions) [3], COYOTE II [2], FIAT (Fully Implicit Ablation and Thermal response code) [3] and so on
FLUENT is used as the Computational Fluid Dynamics (CFD) code as it is capable of modeling the species transport apart from the basic fluid flow [4]
Summary
The hypersonic reentry vehicle is immersed in a hot gas as the kinetic energy of the flow is dissipated by viscous effects. Numerical simulation of the heat transfer during the reentry flight and the material thermal response of the TPS can be challenging due to the multiphysics interactions like chemically reacting flow, radiation and heat conduction. It was identified that aero thermal heat flux prediction and material thermal response is evaluated using in house codes like SACCARA (Sandia Advanced Code for Compressible Aerothermodynamics Research and Analysis) [2], GIANTS (Gauss-Siedel Implicit Aerothermodynamic Navier-Stokes code with thermo chemical surface conditions) [3], COYOTE II [2], FIAT (Fully Implicit Ablation and Thermal response code) [3] and so on. With the advances in commercial Computational Fluid Dynamics (CFD) and Finite Element Analysis (FEA) codes, the prediction of aero thermal heat flux and the material thermal response of the TPS using these codes are highly feasible. The chemically reacting hypersonic flow for an axisymmetric vehicle at zero degree angle of attack is solved using FLUENT and in the current work
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