中文摘要：

用Ma∞=7风洞试验的方法研究了一种吸气式高超声速飞行器二维进气道/内流道的流场特征与起动特性.试验结果表明：在来流总压0.5～1.9 MPa、单位雷诺数2.48×10^6～7.95×10^6范围内,进气道起动的前提下,进气道/内流道沿程压力分布受来流总压、雷诺数的影响变化很小;在进气道外压缩段流动未受干扰前进气道隔离段最大可承受反压约为250倍自由来流压力;未加侧板时该进气道具有自起动能力,加侧板后隔离段出口压力有所增加;在设计点工况,该进气道增压比42.9,总压恢复0.27,出口马赫数2.76.

英文摘要：

　The flow field structure and starting characteristics of two-dimensional inlet/internal flowpath for an airbreathing hypersonic vehicle was analyzed using Ma∞=7 wind tunnel test method.The experimental results show that：if the inlet flowpath is started under incoming total pressure（0.5～1.9 MPa） and unit Reynolds number（2.48×10^6～7.95×10^6l/m）,the variation of the incoming total pressure and Reynolds number has little effect on the static pressure distributions along inlet/internal flowpath;the inlet-isolator could withstand maximum back pressure 250 times the free-stream static pressure,before flow in the inlet compression section is disturbed;the inlet has a self-starting ability if no lateral plate is added,and the outlet pressure at the isolator increases if lateral plates are added before the cowl;under the working condition at the design point,the inlet flowpath has a compression ratio 42.9,total pressure recovery of 0.27,and mass-weighted average Mach number of 2.76.