双下侧定几何二元混压式超声速进气道的风洞试验

 针对一种应用于导弹上的冲压发动机用双下侧布局二元混压式超声速进气道气动特性开展了高速风洞试验研究。研究结果表明，随着反压比的提高，进气道总压恢复系数提高，临界状态后结尾激波系能停留在收缩通道内，在稳定亚临界状态下进气道总压恢复系数最高，但流量系数略有降低；随着来流马赫数的增大，进气道总压恢复系数下降，流量系数在小于设计马赫数下逐渐提高，激波贴口后流量系数基本不变；随着迎角的增大，进气道的总压恢复系数和流量系数随之提高，在Ma＝2.5，侧滑角β＝0°，迎角α增大到6°时进气道出现流量堵塞现象,性能降低；随着侧滑角的增大，两个进气道的性能均下降，迎风侧进气道相对背风侧进气道下降更厉害，在Ma＝2.5，α＝2°，β＝2°时背风侧进气道出现流量堵塞,性能降低；小角度滚转对进气道性能影响不大。

Experimental Investigation of Fixed-geometry Two-dimensional Mixed-compression Supersonic Inlet with Twin-inlet 90° Configuration at Venter

The performance of a fixed geometry two dimensional mixed compression supersonic inlet with twin inlet 90° configuration at the venter of the missile is investigated by wind tunnel tests in this article. Results indicate: ①With the increase of back pressure ratio, the total pressure recovery coefficient at the exit of the inlet increases and the terminal shocks can be stabilized at the convergence area of the inlet. During stable subcritical operation, the total pressure recovery coefficient is the highest, but the mass flow ratio decreases slightly. ②The total pressure recovery coefficient declines with the increase of the free stream Mach number, while the mass flow ratio ascends gradually and remains at 1.0 when the oblique shock is attached the cowl lip. ③With the increase of the angle of attack, the total pressure recovery coefficient and the mass flow ratio increase. The inlet cannot be started when the angle of attack α rises to 6°at Ma＝2.5 and the angle of yaw β＝0°. ④With the increase of the angle of yaw, the total pressure recovery coefficient and the mass flow ratio decrease, with more decrease at the windward inlet is decrease more than at the leeward inlet. The inlet cannot be started when β=2° at Ma＝2.5 and α＝2°. ⑤The small angle of roll has very slight impact on the performance of the inlet.