Numerical simulation of radiance effects on the aerodynamic heating of ablative nose with VSL-VBLS method

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Abstract

One of the basic parameter to design the hypersonic noses is the induced radiative heating to wall. During flight trajectory, the magnitude of aerodynamic heating changes. To accurate estimation of it, the different methods, is presented which, the numerical solution of navier stocks, chemical reactions, ablative modeling, species conservation, turbulence modeling, heat transfer equations with the finite volume algorithms is perfect method. Utilizing these solvers for flight trajectory require the high computational memory. Therefore, the finite difference method have been used, and the equations have been translated to curvature coordinate by mapping terms. The non propagation of data from flow downstream is the requirement to select the type of the space marching solver, and combination of viscous shock layer at body and similarity of viscous boundary layer at stagnation point methods are pass the mentioned requirement by using the lucidity assumption of the mixture elements. With utilizing this method, the radiative heating results of this research have been the excellence compliance with similar researchs. The results deviation started at Mach number greather than 40 but, in comparative to test results, the behavior of radiative heating variations in accordance with the curvature distance was more logical than the similar researchs. So, at Mach number smaller than 6, the radiative heating, in comparative to conduction and convection heating, is dispensable.

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Journal of Solid and Fluid Mechanics
Volume 7, Issue 1
March and April 2017
Pages 175-186

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