冲压发动机用轴对称进气道设计和试验

完成了一种Ma=2.5～4.0冲压发动机用超声速轴对称混合式进气道模型的设计,通过数值模拟和风洞试验,获得了马赫数Ma=2.5,3.0,3.5,4.0,攻角α=0°,3°,6°,8°条件下的超声速轴对称混合式进气道性能。试验结果表明,随着马赫数的增加,总压恢复系数大幅度下降,亚临界稳定范围变窄,流量系数逐渐增加;随着攻角的增大,总压恢复系数和流量系数总体都呈降低趋势,在Ma≥3.0,α=6°时,进气道性能的下降小于5%,亚临界稳定范围变窄。

Design and wind tunnel test of an axisymmetric inlet for ramjet engine

The design of an axisymmetic and mixed-compressed inlet model for the ramjet operating Mach number Ma = 2.5～4.0 was conducted. By using numerical simulations and wind tunnel tests, the inlet performance for the operating Mach number Ma =2.5, 3.0, and 4.0 with the angle of the attack (AOA) α = 0° 3° 6°and 8°was obtained. The tests show that with an increase of the flight Mach number, the total pressure recovery coefficient is reduced dramatically, the sub-critical stable operating range is shortened and the mass flow coefficient is increased gradually. In addition, both the total pressure recovery coefficient and the mass flow coefficient tend to drop when increasing the angle of attack. The case of AOA α = 6°and Ma=3.0 causes the inlet performance to drop by less than 5% and the sub-critical stable operating range to be reduced.