1
Department of Aerospace Engineering, Malek Ashtar University of Technology, Tehran,Iran
2
MSC, Aerospace Eng., Malek Ashtar University of Technology,, Tehran, Iran.
Abstract
The accurate analysis of the heat flux entering the surface in reentry vehicles requires the consideration of chemical interactions in its around flow. This paper aims to numerically investigate the heat flux on the surface of reentry vehicles by considering air dissociation to increase the accuracy of the results. In the present study, the effects of the nose radius, half-angle, and free-stream Mach number on the heat flux entering the surface were examined. In order to define the thermodynamic and transitional properties more accurately, in addition to the Blottner model, the kinetic theory in Ansys Fluent commercial software is also used for comparison. The results show that by increasing the Mach number, the dissociation rate in the shock layer and the tip of the nose increased due to the increased temperature. The dissociation, however, was reduced by get away from the stagnation line in the shock layer. Increasing the nose radius and decreasing the semi-angle increased the thickness of the shock layer increased, consequently increasing species dissociation within the shock layer and reducing the heat flux on the surface. The mean difference of heat flux between two Different transport properties was presented with radius and semi-angle variations. In addition, by examining the states of the ideal gas and non-equilibrium gas, it was found that the position of the shock wave on the stagnation-line was halved, and the maximum temperature on the stagnation-line relative to the non-equilibrium solution was increased by 146%.
Ghasemlooy, S., Parhizkar, H., & Khosrovani, L. (2024). Numerical investigation of the heat flux entering the surface of hypersonic bodies by considering air dissociation. Aerospace Knowledge and Technology Journal, 13(1), -.
MLA
Sadjad Ghasemlooy; Hamid Parhizkar; Lida Khosrovani. "Numerical investigation of the heat flux entering the surface of hypersonic bodies by considering air dissociation". Aerospace Knowledge and Technology Journal, 13, 1, 2024, -.
HARVARD
Ghasemlooy, S., Parhizkar, H., Khosrovani, L. (2024). 'Numerical investigation of the heat flux entering the surface of hypersonic bodies by considering air dissociation', Aerospace Knowledge and Technology Journal, 13(1), pp. -.
VANCOUVER
Ghasemlooy, S., Parhizkar, H., Khosrovani, L. Numerical investigation of the heat flux entering the surface of hypersonic bodies by considering air dissociation. Aerospace Knowledge and Technology Journal, 2024; 13(1): -.
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