Abstract
Numerical simulations are thoroughly carried out for the flows in the nozzle and the test section in the T2 shock tunnel facility. In order to solve the flow realistically, an unsteady, axisymmetric, and nonequilibrium flow solver is employed. The thermochemical states of the gas are described by a four-temperature model. Obtained temperatures are compared with the experimental data measured by Palma using a Planar Laser-Induced Fluorescence (PLIF) Imaging technique.
| Original language | English (US) |
|---|---|
| Title of host publication | Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting |
| Pages | 6931-6938 |
| Number of pages | 8 |
| Volume | 10 |
| State | Published - 2006 |
| Externally published | Yes |
| Event | 44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States Duration: Jan 9 2006 → Jan 12 2006 |
Other
| Other | 44th AIAA Aerospace Sciences Meeting 2006 |
|---|---|
| Country/Territory | United States |
| City | Reno, NV |
| Period | 01/9/06 → 01/12/06 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering