RBCC进气道双流道变几何方案研究

提出了一种基于双流道变几何的二元进气道设计方案:通过下流道的开关，实现进气道压缩角和收缩比的调节，使得进气道能够适应更宽的工作范围，并能兼顾与飞行器和燃烧室的一体化设计.研究表明:该方案可在保证原有双模态冲压发动机进气道高来流马赫数性能不变的前提下，将自起动马赫数降至引射/亚燃模态过渡点附近，该方案自起动马赫数为2.8；低来流马赫数时进气道具有较高的流量系数（来流马赫数为3.0时达到0.62）、较高的总压恢复系数（来流马赫数为3.0时达到0.79）和较低的阻力（低来流马赫数时降低了30%多）. 

Investigation of variable geometry RBCC inlet with double passage

A two-dimensional inlet variable geometry scheme with double passage regulation was put forward. The regulation of inlet compress angle and contraction ratio was achieved by the switch of the downstream compress passage to accommodate wide operation range, and the integrative design with aircraft and combustion was also considered. The investigation shows that,this scheme can reduce the staring Mach number to near the ejector/ramjet mode transition point; the starting Mach number hereto is 2.8; higher total pressure recovery coefficient of 0.62 at coming flow Mach number of 3.0, higher mass flow rate of 0.79 at coming flow Mach number of 3.0, and lower resistance are attained during low coming flow Mach number range (which is reduced to more than 30%), while the inlet performance during high coming flow Mach number range is unvaried.