Investigation of shock-shock interaction in hypersonic rarefied flow using direct simulation Monte Carlo method

TL;DR

This study uses DSMC simulations to analyze shock-shock interactions in hypersonic rarefied flows over a wedge-cylinder, revealing how increasing flow rarefaction diminishes shock interaction effects and alters surface load distributions.

Contribution

It provides detailed insights into shock-shock interactions across a range of Knudsen numbers using DSMC, including validation against experiments and analysis of flow pattern changes with rarefaction.

Findings

Shock-shock interaction features diminish with increasing Knudsen number.

Augmentation factors for shear stress and heat flux decrease as flow becomes more rarefied.

At high Knudsen numbers, augmentation factors fall below unity.

Abstract

The rarefied flows encountered by the hypersonic vehicles in their high-altitude flights call for investigations coupling the shock-shock interaction and the rarefied-gas effect. An in-house direct simulation Monte Carlo (DSMC) solver is employed to simulate a series of hypersonic air flows over a wedge-cylinder configuration at the freestream Mach number of 10. The DSMC simulations cover 15 different Knudsen numbers, spanning from 0.006688 to 0.6688. At the lowest Knudsen number, the numerical results are validated by the corresponding wind-tunnel experiment, and demonstrate the features of an Edney type IV shock-shock interaction, including the type IV wave pattern, the supersonic jet impingement, the augmentations of surface shear stress, pressure and heat flux, as well as the shifts in the angular positions of the peak shear stress, pressure and heat flux over the cylinder surface. In ascending order of Knudsen number, the overviews and details of the flow fields with and without shock-shock interaction, as well as the distributions of the shear stress, pressure and heat flux over the cylinder surface are displayed and analyzed. The increase of flow rarefaction continuously alters the flow pattern of the shock-shock interaction, in which the wave system gradually losses the abilities to deflect the streamlines or to concentrate the energy in the flow. As the flow becomes more rarefied, the shock-shock interaction will result in smaller augmentation factors and less angular shifts of the peak aerodynamic/aerothermal loads. At the highest Knudsen number in this study, the augmentation factors for skin friction and heat flux are found to be less than unity. The existence/vanishment of the supersonic jet and its position relative to the cylinder account for the distribution characteristics of aerodynamic/aerothermal loads over the cylinder surface.