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升力体气动布局 ,由于其良好的高超声速气动特性、有效的内部空间和有益的防热特性 ,越来越受到气动工作者的重视 ,本文应用张涵信院士的NND格式思想 ,用数值模拟的方法对类似于美国X 33的升力体外形进行了气动力、气动热研究。特别是在粘性项的离散和表面热流率的计算中应用了散度和梯度的积分定义 ,避免了数值计算的奇异性 ,保证了通量守恒 ,提高了计算效率。结果表明气动热计算结果与美国同类飞行器结果接近 ,驻点热流率与经典理论结果一致。
Due to its good hypersonic aerodynamic characteristics, effective interior space and beneficial heat-proof characteristics, the aerodynamic body layout of lift body is more and more emphasized by aerodynamic workers. This paper applies the idea of NND format of Academician Zhang Han-xin and numerically simulates Aerodynamic, aerodynamic thermal studies were performed on a lift body shape similar to the U.S. X33. In particular, the integral definition of divergence and gradient is applied in the calculation of discrete and surface heat flow rate of viscous term, which avoids the singularity of numerical calculation, ensures the flux conservation and improves the computational efficiency. The results show that the calculated results of aerodynamic heat are close to the results of similar aircraft in the United States. The stagnation heat flux is consistent with the classical theory.