Computation of hypersonic re-entry flow

Abstract

This project presents a computational study of hypersonic reentry flow over a blunt body. Fluent™ computational fluid dynamics software will be used to simulate the flow over a cylinder in 2 different conditions. The first set of simulations involves reentry flow at 65km at a Mach number of 22. The second set involves nitrogen gas flow at a speed of Mach number 6.14. The heat flux distribution over the cylinder is the main area of study in this project. The distributions are then compared to results validated by previous studies and research.

Different models for the chemistry kinetics, specific heats, viscosities, thermal conductivities and mass diffusivities are being explored. Both the Dunn-Kang and Park Model can be used as the chemistry model as they do not yield significantly different results. Similarly, the “new” and “old” form of Gordon-McBride specific heat functions can be used to define the specific heats of the species in a mixture. This project also finds that the viscosities, thermal conductivities and mass diffusivities of gas species are important. Kinetic theory should be used to define species viscosity and thermal conductivity, as well as mixture mass diffusivity. If the correct set of parameters is used, Fluent™ is able to compute accurate results in the stagnation region.