Abstract
High-fidelity modeling tools are essential for accurate predictions of planetary entry. The same tools can also be used to interpret ground test data. A hypersonic aerothermodynamic computational fluid dynamic code is used to compute the flowfield of a high-enthalpy flow facility, and the results are compared to published experimental data. A test case is selected that consists of a 6.5MJ=kg bulk enthalpy flow that discharges into a vacuum chamber at 0.228 kPa. The simulation parameters are compared to radial and axial velocity profiles. Surface pressure and heat flux profiles are analyzed, and excellent agreement is found with the experimental data. A parametric study is carried out in order to better assess the effects of the initial and boundary conditions.
| Original language | English |
|---|---|
| Pages (from-to) | 393-403 |
| Number of pages | 11 |
| Journal | Journal of Thermophysics and Heat Transfer |
| Volume | 34 |
| Issue number | 2 |
| DOIs | |
| State | Published - 2020 |
Bibliographical note
Funding Information:Financial support for this work was provided by the NASA SpaceTech-REDDI ESI Award NNX16AD18G and the Kentucky Space Grant Graduate Fellowship NNX15AR69H. The computational resources used for this work were supported in part by the National Science Foundation under grant ACI-1626364. The authors greatly appreciate the help of R. S. C. Davuluri at the University of Kentucky. Many thanks to S. Splinter from NASA Langley Research Center for providing details of the nozzle geometry and T. Gokçen from NASA Ames Research Center for his guidance with the nozzle flow conditioning.
Publisher Copyright:
© 2019 by Ümran Düzel, Olivia M. Schroeder, Huaibao Zhang, and Alexandre Martin.
ASJC Scopus subject areas
- Condensed Matter Physics
- Aerospace Engineering
- Mechanical Engineering
- Fluid Flow and Transfer Processes
- Space and Planetary Science