Abstract
The hypersonic rarefied gas flow over blunt bodies in the transitional flow regime, typical of the reentry flight of space vehicles at altitudes higher 90-100 km, is investigated. As an example, the problem of hypersonic flows over long blunt wings and axisymmetric bodies is considered. It is analyzed in a wide range of the free stream Knudsen number by using various approaches: the continuum approach-numerical and analytical solutions, the direct simulation Monte Carlo method and the direct numerical solution of the Boltzmann kinetic equation with the S-model collision integral. The efficiency, domain of applicability, advantages and disadvantages of various approaches in the transitional flow regime are considered. © 2012 American Institute of Physics.
Original language | English |
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Title of host publication | AIP Conference Proceedings|AIP Conf. Proc. |
Publisher | American Institute of Physics |
Pages | 1500-1506 |
Number of pages | 6 |
Volume | 1501 |
ISBN (Print) | 9780735411159 |
DOIs | |
Publication status | Published - 2012 |
Event | 28th International Symposium on Rarefied Gas Dynamics 2012, RGD 2012 - Zaragoza Duration: 1 Jul 2012 → … |
Conference
Conference | 28th International Symposium on Rarefied Gas Dynamics 2012, RGD 2012 |
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City | Zaragoza |
Period | 1/07/12 → … |
Keywords
- continuum model
- heat transfer
- Hypersonic rarefied flow
- s-model collision integral
- transitional regime