A numerical study on a reduction of aerodynamic heating by opposing jet in supersonic and hypersonic flow has been conducted. Flow field around a hemisphere model is calculated in the free stream of Mach number of 4 ands 8. The coolant gas is injected through the nozzle at the nose of the model. In numerical analysis, axisymmetric Navier-Stokes equations are solved with k-ω turbulence model. Flow structures at various conditions are investigated and flow mechanisms of reduction of aerodynamic heating are revealed. Also optimal jet conditions for the reduction of aerodynamic heating are obtained. According to the investigation of various conditions of opposing jet, important phenomena of flow field and some effective jet conditions are found. It becomes clear that a performance of the thermal protection system by opposing jet is greatly affected by jet conditions.
|Number of pages||16|
|Journal||Memoirs of the Faculty of Engineering, Kyushu University|
|Publication status||Published - Mar 1 2006|
All Science Journal Classification (ASJC) codes
- Atmospheric Science
- Earth and Planetary Sciences(all)
- Management of Technology and Innovation