Abstract
In the present study, aerodynamic heating reduction due to opposing jet from the top of blunt body is experimentally and numerically investigated. Experiments are conducted by using a conventional blowdown type wind tunnel. In the experiments, a hemisphere model is installed into supersonic free stream of Mach number of 4 and the coolant N2 gas is injected through a nozzle. Significant decreases of surface heat flux are obtained and opposing jet is proved to be effective on aerodynamic heating reduction at the nose of the blunt body. Numerical analysis is conducted in order to understand more detailed flow field. In numerical analysis, axisymmetric full Navier-Stokes equations are solved by an implicit finite difference method. LU-ADI and AUSM-DV scheme are used. Numerical results show good agreements with experiments and more detailed investigation of the flow indicates that the most effective aerodynamic heating reduction is occurred in the recirculation region.
| Original language | English |
|---|---|
| Title of host publication | 40th AIAA Aerospace Sciences Meeting and Exhibit |
| Publication status | Published - 2002 |
| Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: Jan 14 2002 → Jan 17 2002 |
Other
| Other | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
|---|---|
| Country/Territory | United States |
| City | Reno, NV |
| Period | 1/14/02 → 1/17/02 |
All Science Journal Classification (ASJC) codes
- Space and Planetary Science
- Aerospace Engineering