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RVSPHR是一种确定弹道再入飞行器无粘气动力和表面热流率的近似数值计算程序。在头部亚跨音速区内,由工程方法给出激波角及压力分布,并假定激波层内的物面法向压力和法向速度剖面,而相应的激波形状则按质量守恒条件迭代调整。下游超音速区仍由严格运动方程差分数值求解。在无粘流计算的基础上,用无需迭代的熵吞技术,计算表面热流率。所有计算结果与严格数值解及实验值作了比较,其一致性较好。
The RVSPHR is an approximate numerical calculation program to determine the non-sticking force and surface heat flow rate of a ballistic reentry aircraft. In the head sub-sonic region, the shock wave angle and pressure distribution are given by engineering method, and the normal pressure and normal velocity profile of the object plane in the shock wave layer are assumed, and the corresponding shock wave shape is calculated according to the conservation of mass condition Iteration adjustment. The downstream supersonic region is still solved by the differential equations of the rigorous equations of motion. On the basis of non-viscous flow calculation, surface heat flow rate is calculated by entropy swallowing without iteration. All calculations are compared with the strict numerical solution and experimental values, and the consistency is good.