Design Of Supersonic Combustion Wind Tunnel And Numerical Simulation Of Its Flow

Recently, with the development of aerospace industry,more and more people pay great enthusiasm at exploration and research of high-speed aircraft.Scramjet is a new ramjet technology that is compare to flight mach number is greater than 6 and whose core technology is supersonic combustion. Its application background is hypersonic cruise missiles, hypersonic aircraft and space plane, etc. Ramjet has the following advantages: It can use oxygen which in the atmosphere as oxidant, so when the ramjet is in hypersonic flight, the economic performance was significantly better than turbojet engines and rocket engine. There are not rotational components in the engine, also it has simple structure, the small quality, low cost, and high trust-weight. But with promotion of flying velocity, many problems have appeared that is brought with supersonic flow.For example: Aerodynamic heated, the interference of shockwave-boundary layer in inlet, high-speed mixing in chamber, etc. That is why more research about supersonic flow is needed. This paper mainly discusses the construction of supersonic wind tunnel, the aerodynamic calculation about system, the determination of the paremeter and selection of equipment, etc. Through the computation through business Software FLUENT, It turn out that the nozzle curve that using the specific method has the uniform distribution in outlet. It meets the designed Mach number, and meets the requirements of future tests. Also this paper analys the interference phenomena of shock-boundary layer qualitatively through the numerical calculation. It explains that the small promotion of velocity backward the shock is due to the thickness in boundary layer.This paper also calculates the structure of sweep slope in the combustion chamber through the FLUENT software. The results show that: 1, the effect of sweep ramp structure to the mixing is greater than that has not sweep ramp, The intensity of vortex is greater too, The bigger of the sweep ramp angle, the better.2, The loss of the total pressure in the combustion chamber which has the sweep ramp structure is bigger than that has not sweep ramp structure and It will more bigger when the sweep ramp angle is increasing. 3, In order to enhance the mixing in the combustion chamber and guarantee a higher total pressure recovery at the same time, It is not appropriate to make big sweep ramp angle,about 10°is better.