基于边界层理论的球头驻点热流计算方法研究

doi:10.7527/S1000-6893.2024.30448

Abstract

Abstract: It is very important for aircraft thermal protection design to accurately know the heat flux at the stagnation point of spherical head. Based on the assumption of self-similar boundary layer at the stagnation point of equilibrium air, the boundary layer equations are derived. The fourth-order Runge-Kutta method is used to numerically solve the deformed ordinary differential boundary layer equations, and the forward approximation shooting method is established to find the optimal solution of the equations. Thus, the method for solving the boundary layer equations and calculating the stagnation point heat flux of the spherical head is established, and good comparison results are obtained with the experimental values. Based on this method, for 182 working conditions of height 10km ~ 60km, different velocity and different wall temperature, the calculation deviation of heat flux formula of spherical stagnation point under Fay-Riddell equilibrium flow condition is analyzed. It is found that in most working conditions, the calculation deviation of heat flux increases obviously when the wall temperature approaches the outer edge temperature of boundary layer. New heat flux formulas for spherical stagnation point are obtained by fitting the dimensionless parameters into a combination of several dimensionless parameters. The heat flux calculation results are compared under several working conditions, and the application results are better than those of the spherical stagnation point heat flux formula under Fay-Riddell equilibrium flow condition.

Key words: boundary layer theory, laminar flow self-similarity, spherical head, stagnation heat flux, equilibrium flow, Aerodynamic heat

CLC Number:

V211.19

References

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Study on Calculation Method of Heat Flow at Stagnation Point of Spherical Head Based on Boundary Layer Theory

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