不同壁温及差分格式下超燃冲压发动机的仿真

doi:10.7527/S1000-6893.2021.26353

Abstract

Abstract: In this paper, numerical simulation is carried out for circular scramjet with different wall temperature conditions and difference schemes, and their influence on the numerical results is investigated. The results show that the widely used adiabatic wall boundary condition will lead to the overestimation of the recirculation zone at the interaction position of shock and boundary layer; the flow path contracts and the wall pressure increases. Using high-precision difference scheme cannot calculate the size of recirculation area more accurately, would instead, aggravate the boundary layer separation. The recirculation zone at the interaction position of shock and boundary layer can be minimized when adopting the isothermal wall of 300 K. The simulation results are in good agreement with the experimental results. The numerical results show that for the current configuration, blindly improving the accuracy of the numerical scheme does not get better results. On the contrary, it could make the simulation deviate from the experiment. If the wall temperature conditions are properly modified, perfect simulation results can be obtained even if the accuracy of the numerical scheme is low. Finally, according to the simulation result which is consistent with the experiment, the flow field characteristics of circular scramjet are analyzed, with emphasis on the cavity shear layer and the mass exchange characteristics.

Key words: scramjet, wall temperature condition, difference scheme, circular, supersonic

CLC Number:

V411.3
V239

MA Guangwei, SUN Mingbo, ZHAO Guoyan, LI Fan, LIANG Changhai, CHEN Huifeng. Simulation of scramjet with different wall temperatures and difference schemes[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726353-726353.

References

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Simulation of scramjet with different wall temperatures and difference schemes

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