Numerical simulation of aerodynamic heating reduction due to opposing jet in hypersonic flow
In supersonic flight, severe aerodynamic heating is risen at the nose of blunt body caused ablation. Therefore accurate prediction of aerodynamic heating and construction of proper thermal protection system are required. The numerical study on a reduction of aerodynamic heating by opposing jet has been conducted. Flow field around a hemisphere model is calculated in supersonic free stream of Mach number 3.98 and the coolant gas is injected through the nozzle at the nose the model. CFD method was Finite Volume Method for time integration be used, axisymmetric full Navier-Stokes equations were applied as governing equations and k-ε turbulence model is used. Numerical simulation demonstrated, compared with no jet, the reduction of aerodynamic heating due to opposing jet was to be proved quite effective at the nose of blunt body. Numerical simulation investigations show that, as the pressure ratio is increased, caused the wall pressure and heat flux decrease, and recirculation region size largen, effective reduction of the aerodynamic heating remarkably. As the opposing nozzle diameter ratio was decreased, the pressure and heat flux increased, and recirculation region size lessening, the effect of reduction aerodynamic heating was reduced.
opposing jet aerodynamic heating numerical simulation
H.Y.Li Q.T.Eri
Thermal Division, Changcheng Institute of Metrology & Measurement, Beijing, 100095 China School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing, 100083, China
国际会议
The Fifth International Conference on Fluid Mechanics(第五届国际流体力学会议)
上海
英文
2007-08-15（万方平台首次上网日期，不代表论文的发表时间）