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Study on the performance of spatial discretization schemes for hypersonic flow

机译：超音速流空间离散方案性能研究

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Purpose - With the continuous increase of space activities and insight into space exploration, the velocity of near space hypersonic vehicles becomes higher and higher, which leads to the aerothermodynamic phenomenon getting worse around a vehicle; therefore, the exploration of numerical scheme applicability is essential for hypersonic flow simulations. Design/methodology/approach - The implicit finite volume schemes are derived from axisymmetric Navier-Stokes equations for chemical equilibrium flow and programmed in Fortran. Taking the atmosphere at 30 km as an example, the performance of spatial discretization schemes such as AUSMPW and AUSMPW+ are analyzed in a range of Mach numbers from 17 to 32. Findings - The AUSMPW scheme appears pressure jump near the stagnation if the Mach number is over 18, but AUSMPW+ scheme shows better performance in comparison. Originality/value - This study will help the aerothermodynamic design in near space hypersonic vehicles.
机译：目的-随着空间活动的不断增加和对太空探索的了解，近空间高超声速飞行器的速度越来越高，导致飞行器周围的空气热力学现象越来越严重；因此，探索数值方案的适用性对高超音速流模拟至关重要。设计/方法/方法-隐式有限体积方案是从用于化学平衡流的轴对称Navier-Stokes方程派生的，并在Fortran中进行了编程。以30 km处的大气为例，分析了空间离散化方案（如AUSMPW和AUSMPW +）在马赫数从17到32的范围内的性能。结果-如果马赫数是超过18，但相比之下AUSMPW +方案表现出更好的性能。原创性/价值-这项研究将有助于近空间超音速飞行器的空气动力学设计。

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