Length-to-Depth Ratio Effects on Aerodynamic Surface Quantities of a Rarefied Hypersonic Gap Flow

Abstract

Numerical simulations of two-dimensional steady-state hypersonic flow in a gap at different length-to-depth (L/H) ratio are performed by using a Direct Simulation Monte Carlo (DSMC) method. The work focuses on the effects in the aerodynamic surface quantities, such as heat transfer, pressure and skin friction coefficients due to variations in the gap L/H ratio. The analysis showed that aerodynamic surface quantities presented a large dependence on the L/H ratio for the range investigated. It was found that heat transfer, pressure, and skin friction coefficients presented the maximum values along the gap downstream face, more precisely, at the vicinity of the gap shoulder. Furthermore, simulations showed that pressure and heating loads are several times larger than those for a smooth surface.

Numerical Simulation of Supersonic Gap Flow

“…Hinderks et al [ 7 ] investigated hypersonic flow with consideration of fluid structure interaction, where the flow field was supposed as laminar flow, and chemical non-equilibrium conditions were adopted in the calculation. Paolicchi et al [ 8 ] used the direct simulation Monte Carlo method to do numerical simulation of two-dimensional steady-state hypersonic rarefied flow in a gap at different width-to-depth ratios and wall temperatures. Yang et al [ 9 ] developed a hypersonic aero-thermal simulation method for missile flight.…”