Application of flow splitting schemes ROE and AUSM to supersonic aerodynamics problems

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To verify the ANSYS FLUENT software package (TsAGI license N 501024) we solve the problem of decay of the discontinuity of the parameters of an inviscid onedimensional gas flow in a nonstationary setting and compare it with the exact analytical solution. We consider two discretization schemes for convective flows, viz. Roe FDS (Roe Flux-Difference Splitting Scheme) and AUSM (Advection Upstream Splitting Method). The influence of the order of spatial approximation on the accuracy of the numerical solution is evaluated, including using the MUSCL (Monotone Upstream-Centered Schemes for Conservations Laws) approach. The nominal order of accuracy can be achieved in nondiscontinuous solutions only, and in places of discontinuity the accuracy decreases, and the order of accuracy obtained in this work does not exceed 1.5. If the nominal order of accuracy can be achieved in nondiscontinuous solutions only, and in places of discontinuities the accuracy decreases according to the estimates made, the grid order of accuracy obtained does not exceed 1.5. We make a comparative analysis of the performance of the considered schemes in the problem of practical aerodynamics, viz. the supersonic flow around a flat air intake device at Mach number MTO = 2.41. It is shown that in the ANSYS FLUENT calculation package it is advisable to use the ROE scheme of the second order of accuracy since the time spent on the calculation is 5-9% less compared to the AUSM scheme of the second and third orders of accuracy with the same level of error in the numerical solution.

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Verification, numerical simulation, roe scheme, ausm scheme, muscl reconstruction, discontinuity decay problem, supersonic intake

Короткий адрес: https://sciup.org/142238154

IDR: 142238154

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