Location
Havener Center, St. Pat's Ballroom C
Presentation Date
April 21, 2023, 3:15pm-4:15pm
Session
Session 4
Description
The Hypersonic International Flight Research Experimentation (HIFiRE) program 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 flow contours. The flow field studied is for Mach number 7.18 and an angle of attack (α) of 2°. The flow field 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 that closely match the computational results presented at the 2022 High-Fidelity CFD Workshop within 5% for α = 2°.
Meeting Name
32nd Annual Spring Meeting of the NASA-Mo Space Grant Consortium
Document Type
Presentation
Document Version
Final Version
File Type
text
Language(s)
English
Rights
© 2023 The Authors, all rights reserved.
Computational Analysis of the HIFiRE-1 Hypersonic Test Model in ANSYS Fluent
Havener Center, St. Pat's Ballroom C
The Hypersonic International Flight Research Experimentation (HIFiRE) program 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 flow contours. The flow field studied is for Mach number 7.18 and an angle of attack (α) of 2°. The flow field 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 that closely match the computational results presented at the 2022 High-Fidelity CFD Workshop within 5% for α = 2°.
