Abstract
The hypersonic flow of nitrogen gas over a double wedge was simulated by the DSMC method using two-dimensional and three-dimensional geometries. The numerical results were compared with experiments conducted in the HET facility for a high-enthalpy pure nitrogen flow corresponding to a free stream Mach number of approximately seven. Since the conditions for the double wedge case are near-continuum and surface heat flux and size of the separation are sensitive to DSMC numerical parameters special attention was paid to the convergence of these parameters for both geometries. At the beginning of the simulation, the separation zone was predicted to be small and the heat flux values for the 2-D model were comparable to the experimental data. However, for increasing time, it was observed that the heat flux values and shock profile strongly deviated from the experiment. Investigation of a three-dimensional model showed that the flow is truly three-dimensional and the side edge pressure relief provides good agreement between simulations and the experiment.
| Original language | English (US) |
|---|---|
| Title of host publication | 30th International Symposium on Rarefied Gas Dynamics, RGD 2016 |
| Editors | Henning Struchtrup, Andrew Ketsdever |
| Publisher | American Institute of Physics Inc. |
| ISBN (Electronic) | 9780735414488 |
| DOIs | |
| State | Published - Nov 15 2016 |
| Event | 30th International Symposium on Rarefied Gas Dynamics, RGD 2016 - Victoria, Canada Duration: Jul 10 2016 → Jul 15 2016 |
Publication series
| Name | AIP Conference Proceedings |
|---|---|
| Volume | 1786 |
| ISSN (Print) | 0094-243X |
| ISSN (Electronic) | 1551-7616 |
Other
| Other | 30th International Symposium on Rarefied Gas Dynamics, RGD 2016 |
|---|---|
| Country | Canada |
| City | Victoria |
| Period | 7/10/16 → 7/15/16 |
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Keywords
- DSMC
- Hypersonic separated flows
- Shock-wave boundary layer interactions
ASJC Scopus subject areas
- Ecology, Evolution, Behavior and Systematics
- Ecology
- Plant Science
- Physics and Astronomy(all)
- Nature and Landscape Conservation
Cite this
Modeling of near-continuum laminar boundary layer shocks using DSMC. / Tumuklu, Ozgur; Levin, Deborah A.; Gimelshein, Sergey F.; Austin, Joanna M.
30th International Symposium on Rarefied Gas Dynamics, RGD 2016. ed. / Henning Struchtrup; Andrew Ketsdever. American Institute of Physics Inc., 2016. 050004 (AIP Conference Proceedings; Vol. 1786).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Modeling of near-continuum laminar boundary layer shocks using DSMC
AU - Tumuklu, Ozgur
AU - Levin, Deborah A.
AU - Gimelshein, Sergey F.
AU - Austin, Joanna M.
PY - 2016/11/15
Y1 - 2016/11/15
N2 - The hypersonic flow of nitrogen gas over a double wedge was simulated by the DSMC method using two-dimensional and three-dimensional geometries. The numerical results were compared with experiments conducted in the HET facility for a high-enthalpy pure nitrogen flow corresponding to a free stream Mach number of approximately seven. Since the conditions for the double wedge case are near-continuum and surface heat flux and size of the separation are sensitive to DSMC numerical parameters special attention was paid to the convergence of these parameters for both geometries. At the beginning of the simulation, the separation zone was predicted to be small and the heat flux values for the 2-D model were comparable to the experimental data. However, for increasing time, it was observed that the heat flux values and shock profile strongly deviated from the experiment. Investigation of a three-dimensional model showed that the flow is truly three-dimensional and the side edge pressure relief provides good agreement between simulations and the experiment.
AB - The hypersonic flow of nitrogen gas over a double wedge was simulated by the DSMC method using two-dimensional and three-dimensional geometries. The numerical results were compared with experiments conducted in the HET facility for a high-enthalpy pure nitrogen flow corresponding to a free stream Mach number of approximately seven. Since the conditions for the double wedge case are near-continuum and surface heat flux and size of the separation are sensitive to DSMC numerical parameters special attention was paid to the convergence of these parameters for both geometries. At the beginning of the simulation, the separation zone was predicted to be small and the heat flux values for the 2-D model were comparable to the experimental data. However, for increasing time, it was observed that the heat flux values and shock profile strongly deviated from the experiment. Investigation of a three-dimensional model showed that the flow is truly three-dimensional and the side edge pressure relief provides good agreement between simulations and the experiment.
KW - DSMC
KW - Hypersonic separated flows
KW - Shock-wave boundary layer interactions
UR - http://www.scopus.com/inward/record.url?scp=85008913718&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85008913718&partnerID=8YFLogxK
U2 - 10.1063/1.4967554
DO - 10.1063/1.4967554
M3 - Conference contribution
AN - SCOPUS:85008913718
T3 - AIP Conference Proceedings
BT - 30th International Symposium on Rarefied Gas Dynamics, RGD 2016
A2 - Struchtrup, Henning
A2 - Ketsdever, Andrew
PB - American Institute of Physics Inc.
ER -