高速风洞发动机进排气动力模拟试验技术

Simulated test technique for engine air intake and exhaust in high speed wind tunnel

为了研究该项试验技术,对发动机动力模拟器(TPS、引射器等)和发动机进排气模拟参数进行了分析和比较.采用理想流体一元管流理论,建立了引射器的理论计算方法.结合某埋入式进气道航弹的发动机进排气动力模拟风洞试验,采用引射式动力模拟器(引射器最大外径设计为41mm) ,在FL- 7高速风洞开展了国内首次发动机进排气同时模拟的试验技术研究.试验结果表明:来流马赫数和排气落压比达到1 0 0 %模拟,进气流量系数实现89%的模拟.进排气影响使某埋入式进气道航弹的升力和阻力增加、引起低头力矩,有无动力底阻系数均为负值.

To study this test technique, the engine simulator (turbine powered simulator, ejectors) and the simulated parameters were analyzed and compared firstly in this paper. The Calculating methods of the ejector were presented using the theoretical base of One-dimensional ideal flow. An engine air intake and exhaust simulation experiment of a cruise missile with the ejector (the maximum diameter of the ejector is 41 mm) was conducted in the FL-7 transonic wind tunnel. The test results showed that the free stream Mach number and nozzle pressure ratio getting 100% simulated, the flux coefficient realizing 89% simulated. The air intake and exhaust can increase the value of lift and drag, simultaneously the value of pitching moment was decreased, the value of base drag of the model is negative in no matter which situation whether existing air intake and exhaust or not.