Abstract
Numerical simulations of the HyShot scramjet flows in the T4 shock tunnel experiments are carried out. In order to realistically determine the freestream conditions in the test section, the nozzle flow is calculated by a thermochemical nonequilibrium axisymmetric flow solver. Using the obtained freestream conditions, a flow for the HyShot scramjet model is calculated. The results are compared with the experimental data and the CFD calculated results using the nominal freestream conditions, which are deduced under the thermal equilibrium assumption.
| Original language | English (US) |
|---|---|
| Title of host publication | A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference |
| Pages | 1419-1428 |
| Number of pages | 10 |
| Volume | 2 |
| State | Published - 2005 |
| Externally published | Yes |
| Event | 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference - Capua, Italy Duration: May 16 2005 → May 20 2005 |
Other
| Other | 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference |
|---|---|
| Country/Territory | Italy |
| City | Capua |
| Period | 05/16/05 → 05/20/05 |
ASJC Scopus subject areas
- Engineering(all)