进气道低速特性试验技术研究

Experimental investigation on low speed characteristics of inlet

为了研究多种进气形式进气道的低速稳、动态气动特性,采用引射器引射的方式,在FL 8低速风洞开展了进气道试验技术研究,研制出了进气道试验专用引射系统、流量测量与控制装置、模型支撑连接装置及大迎角试验设备,通过机翼下、腹部和翼根三种进气形式的进气道模型风洞试验对新研制的进气道试验设备和相关试验技术进行了验证。试验结果表明:在零速度和大迎角、大侧滑(α=60°,β=20°)低速来流下,利用多喷嘴引射器引射可以很好地实现各种进气道模型内流场的模拟,保证进气道工作线与发动机工作线相交。

To investigate the static and dynamic characteristics of several forms of inlet, injection by the injector was adopted. The studies of inlet test technique were developed in the FL-8 low speed wind tunnel, and special inject system in inlet test, mass measurement and control device, model connection and support facility as well as test equipment at high angle of attack were developed. By the three forms of wind tunnel tests, i.e. the inlet model under the wing, the root of wing and the abdomen of an airplane, the inlet test devices and relative test technique were verified. The test results showed that at zero speed and at high angle of attack, high angle of sideslip (α=60°, β=20°) with low speed flow, the simulation of inner flow field of inlet model can be well carried out by the multi-nozzle injector, which meets the requirements of simulating the working envelope lines of inlet and engine.