TY - GEN
T1 - Computational Analysis of the HIFiRE-1 Hypersonic Test Model in ANSYS Fluent
AU - Murphy, Aidan R.
AU - Agarwal, Ramesh K.
N1 - Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA., All rights reserved.
PY - 2022
Y1 - 2022
N2 - 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 nondimensionalized heat flux and static pressure profiles.
AB - 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 nondimensionalized heat flux and static pressure profiles.
UR - http://www.scopus.com/inward/record.url?scp=85135060398&partnerID=8YFLogxK
U2 - 10.2514/6.2022-4047
DO - 10.2514/6.2022-4047
M3 - Conference contribution
AN - SCOPUS:85135060398
SN - 9781624106354
T3 - AIAA AVIATION 2022 Forum
BT - AIAA AVIATION 2022 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA AVIATION 2022 Forum
Y2 - 27 June 2022 through 1 July 2022
ER -