Hypersonic Flow Analysis of Re-entry Vehicles Using Three Dimensional Navier-Stokes Equations

Date

2015-07-27

Author

Özgün, Muharrem
Eyi, Sinan

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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The purpose of this study is to develop an accurate and efficient CFD code that can be used in hypersonic flows. The flow analysis is based on the three dimensional Navier-Stokes equations. The analytical method is used to calculate the Jacobian matrix. Flow parameters and convective heat transfer are analyzed on Apollo AS-202 Command Module. Also, algebraic Baldwin-Lomax turbulence model is used to analyze hypersonic turbulent flow and the one-equation Spalart-Allmaras turbulence model will be implemented since this turbulence model is numerically robust and generally gives good predictions in hypersonic applications.

URI

https://hdl.handle.net/11511/46764

DOI

https://doi.org/10.2514/6.2015-3881

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

M. Özgün and S. Eyi, “Hypersonic Flow Analysis of Re-entry Vehicles Using Three Dimensional Navier-Stokes Equations,” 2015, vol. 2015, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/46764.