Computational Analysis of the HIFiRE-1 Hypersonic Test Model in ANSYS Fluent

Abstract

The Hypersonic International Flight Research Experimentation (HIFiRE) is a program that explores and advances hypersonic aerospace systems by developing a multitude of test flight geometries and conducting experimental test flights to obtain data for use in validation of computational models and results. This study focuses on computational validation of heat flux, and calculation of static pressure profiles, skin friction coefficient profiles and the flow contours. The flow fields studied are for a Mach number 7.18 and angles of attack (α) of 0° & 2°. These flow fields include many compressible flow features such as an expansion wave at the intersection of the cone and flat cylindrical section, an oblique shock wave at the cylinder and flare connection point, and a detached bow shock at the tip of the geometry. These flow features are present in the experimental test flight data as well as in ground test studies conducted in the CALSPAN–University of Buffalo Research Center’s LENS I facility along with computational results presented at the 2022 High-Fidelity CFD Workshop. Computations are performed using the Reynolds-Averaged Navier-Stokes (RANS) equations with one-equation Spalart-Allmaras (SA) turbulence model in ANSYS Fluent with suitable boundary conditions which give results for non-dimensionalized heat flux and static pressure profiles which closely match the computational results presented at the 2022 High-Fidelity CFD Workshop within 5% for α = 2°. For α = 0°, the coarsest mesh produced adequate results, but when refining the mesh, the results deviate from expectation as seen in Mach contours of the flow field as well as non-dimensionalized heat flux and static pressure profiles.