Ghasemloo, S., Noori, S.. (1393). Approximate Viscous Shock-Layer Analysis of Axisymmetric Bodies in Perfect Gas Hypersonic Flow. علوم و فناوری فضایی, 7(1), -.
S. Ghasemloo; S. Noori. "Approximate Viscous Shock-Layer Analysis of Axisymmetric Bodies in Perfect Gas Hypersonic Flow". علوم و فناوری فضایی, 7, 1, 1393, -.
Ghasemloo, S., Noori, S.. (1393). 'Approximate Viscous Shock-Layer Analysis of Axisymmetric Bodies in Perfect Gas Hypersonic Flow', علوم و فناوری فضایی, 7(1), pp. -.
Ghasemloo, S., Noori, S.. Approximate Viscous Shock-Layer Analysis of Axisymmetric Bodies in Perfect Gas Hypersonic Flow. علوم و فناوری فضایی, 1393; 7(1): -.
Approximate Viscous Shock-Layer Analysis of Axisymmetric Bodies in Perfect Gas Hypersonic Flow
In this paper, an approximate axisymmetric method is developed which can reliably calculate fully viscous hypersonic flow over blunt-nosed bodies. In this method, a Maslen’s second-order pressure expression is used instead of the normal momentum equation. The combination of Maslen’s second-order pressure expression and viscous shock layer equations is developed to accurately and efficiently compute hypersonic flow fields of perfect gas around blunt-body configurations. The results show that, this combination leads to more accurate solutions and less extensive computer run times in the preliminary design environment. Furthermore, the utility of Cebeci-Smith turbulence model is adequate for application to long slender bodies. The results of these computations are found to be in good agreement with available numerical and experimental data.
Approximate Viscous Shock-Layer Analysis of Axisymmetric Bodies in Perfect Gas Hypersonic Flow
نویسندگان [English]
S. Ghasemloo؛ S. Noori
چکیده [English]
In this paper, an approximate axisymmetric method is developed which can reliably calculate fully viscous hypersonic flow over blunt-nosed bodies. In this method, a Maslen’s second-order pressure expression is used instead of the normal momentum equation. The combination of Maslen’s second-order pressure expression and viscous shock layer equations is developed to accurately and efficiently compute hypersonic flow fields of perfect gas around blunt-body configurations. The results show that, this combination leads to more accurate solutions and less extensive computer run times in the preliminary design environment. Furthermore, the utility of Cebeci-Smith turbulence model is adequate for application to long slender bodies. The results of these computations are found to be in good agreement with available numerical and experimental data.
کلیدواژهها [English]
Approximate, Aerodynamic heating, HypersonicFlow, Perfect Gas
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