Abstract
A numerical study on a reduction of aerodynamic heating by opposing jet in supersonic flow has been conducted. Flow field around a hemisphere model is calculated in supersonic free stream of Mach number 3.96 and the coolant gas is injected through the sonic nozzle at the nose of the model. In numerical analysis, axisymmetric Navier-Stokes equations are solved by an implicit finite difference method, and k-ω turbulence model is used. Significant decreases of surface heat flux are observed and opposing jet is proved to be effective on aerodynamic heating reduction around a stagnation region of the blunt body. In our previous study, experiments on the reduction of aerodynamic heating by opposing jet in supersonic flow were conducted in wind tunnel. The result of numerical analysis shows good agreement with experiment. Numerical results show that the recirculation region plays an important role for the reduction of heat flux. For the reduction of the aerodynamic heating, it is effective to cover the body surface with the cool jet flow and to form strong circulation region.
| Original language | English |
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| Pages | 11641-11648 |
| Number of pages | 8 |
| DOIs | |
| Publication status | Published - 2005 |
| Event | 43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States Duration: Jan 10 2005 → Jan 13 2005 |
Other
| Other | 43rd AIAA Aerospace Sciences Meeting and Exhibit |
|---|---|
| Country/Territory | United States |
| City | Reno, NV |
| Period | 1/10/05 → 1/13/05 |
All Science Journal Classification (ASJC) codes
- General Engineering