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Author(s): |
Baoguo Wang, School of Aerospace Engineering, Beijing Institute of Technology, Beijing, China
Yeping Sun, School of Aerospace Engineering, Beijing Institute of Technology, Beijing, China
Geng Qian, School of Aerospace Engineering, Beijing Institute of Technology, Beijing, China |
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Abstract: |
An engineering algorithm for the computation of wall heat flux of hypersonic vehicles is presented. There are 3 major steps in the computation of wall heat flux, which are 1) solve hypersonic flow using Euler equation; 2) introduce Cooke’s axisymmetric analogue concept and Chung-Hua Wu’s stream-surface concept; introduce the equilibrium gas assumption and boundary layer assumption to solve boundary layer set of equations under orthogonal coordinates using difference scheme and obtain the velocity profile of boundary layer, obtain relevant flow parameters at outer edge of boundary layer using mass balance approach including entropy change impact. Thermodynamic characteristics and transportation characteristics of high temperature gas have been considered in the computation; 3) choose appropriate engineering approximation formula to compute the wall heat flux. Several approximation formulas have been used in this paper respectively. The computation showed that the method presented in this paper required much less computation, had higher efficiency, and could solve wall heat flux problem of hypersonic vehicles with angle of attack, and satisfy accuracy requirement of engineering design.
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