Hao Weidong, Deng Xueying, Qu Fanglianget al. Simulated test technique for engine air intake and exhaust in high speed wind tunnel[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(04): 459-463. (in Chinese)
Citation: Hao Weidong, Deng Xueying, Qu Fanglianget al. Simulated test technique for engine air intake and exhaust in high speed wind tunnel[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(04): 459-463. (in Chinese)

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

  • Received Date: 14 Oct 2003
  • Publish Date: 30 Apr 2005
  • 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 41mm) 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.

     

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