【摘要】 在小型激波风洞中采用动态压力测量的方法。研究了双燃式液体冲压发动机进气道和燃烧室的冷态内流场。采用连管实验方法,将进气道内压段的起始截面与风洞的型面喷管的出口截面直接相连,在进气道内压段进口截面处,气流马赫数Ma=3.15,雷诺数Re=3.3×10~7/m。内流场中毕托压和静压测量结果表明,在文中实验条件下该冲压发动机模型以双燃式工况运行,外涵道为超音速通道;内涵道(亚燃室)为亚音速通道。在亚燃室中测得的毕托压数值较低,气流总压损失较大。这是由于超音速通道中能量较低的附面层气流全部流入亚燃燃烧室,同时又在亚燃燃烧室进口区出现激波与厚附面层相互作用的结果。实验中还发现隔板的支撑肋对该现象影响不大。更多还原

【Abstract】 The cold internal flow field of the inlet and combustor of a dual-mode scramjet model was investigated by means of pressure measurement in a small shock tunnel. The experiment was conducted by directly connecting the internal inlet of the scramjet model to the exit of a contoured nozzle. The Mach number and Reynolds number were 3.14 and 3.3×10~7 permeter respectively at the exit of the nozzle. The pitot pressures and static pressure measured in the internal flow filed show that the scramjet model does work in dual mode state. However, the pitot pressure in the pilot duct is very low, which means great total pressure loss occurs when the stream flowing from inlet to the pilot duct. It is found that the struts of the splitter plate has little influence to the total pressure loss. Some analysis for the total pressure loss has been made according to the experimental results.更多还原