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CSME 2021/08
Volume 42 No.4
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423-437
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Supersonic Flow Around Asymmetrical Cone of Arbitrary Cross Section at High Temperature
Mohamed Roudane a, Toufik Yahiaoui b and Toufik Zebbiche b
aDepartment of Mechanical Engineering, Faculty of Technology, University of Blida 1, BP 270 Blida 09000, Algeria
bInstitute of Aeronautics and Space Studies, University of Blida 1, BP 270 Blida 09000, Algeria.
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Abstract:
The aim of this work is to develop a new numerical model for calculating a supersonic flow and shock parameters around a 3D cone of arbitrary cross-section at high temperature, below the dissociation threshold of the molecules. The developed method consists to divise the cross section at several points, and considering the calculation of the conical shock parameters, as well as the cone surface parameters in each obtained transverse deviation. The flow deviation along each obtained surface is a function of the incidence angle and the inclination formed by this deflection. The flow parameters calculation on the cone surface is done by solving a system of three coupled differential equations with initial condition by the Runge Kutta method. The calculation of the thermodynamic parameters through the conical shock in each transverse direction is made by solving a modified oblique shock wave equations at high temperature. The flow calculation accuracy depends on the discretization of the cross-section. The computation of the aerodynamic force and moment on the cone surface is done consequently, giving each three components in the three directions of the movement. The application is for air.
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Keywords: Cone. Arbitrary cross section. Incidence angle. High temperature. Calorically imperfect gas. Runge Kutta Method. Air. Aerodynamic force. Aerodynamic moment. Normal Shock. Oblique Shock. Conical Shock.
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*Corresponding author; e-mail: z_toufik270169@yahoo.fr
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©
2021
CSME , ISSN 0257-9731
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