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本文采用TSDH方程计算三维后掠机翼的跨音速绕流,考虑了适用于机翼钝前缘的前缘边界条件和前缘速势方程。采用Jameson格式在不等步长格网中的推广形式,把TSDH方程离散化为差分方程组。然后,在整个计算空间内布置稀网,在机翼附近再布置密网,进行稀密网的交替迭代,以加速收敛和提高计算精度。对ONERA M6机翼的超临界无激波和有激波情况的计算表明,TSDH解与FVP解和风洞试验符合良好。
In this paper, the TSDH equation is used to calculate the transonic flow around a three-dimensional swept backfoil. The boundary conditions of the leading edge and the leading edge velocity equation are considered. Using the generalized Jameson format in the unequal stride lattice, the TSDH equation is discretized into a system of difference equations. Then, a thin net is arranged in the entire calculation space, and a dense net is arranged near the airfoils so as to alternately iterate the dense net to accelerate the convergence and improve the calculation precision. Calculations of the ONERA M6 wing’s supercritical shock and shock show that the TSDH solution is in good agreement with the FVP solution and the wind tunnel test.