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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2016, Vol. 37 ›› Issue (11): 3263-3272.doi: 10.7527/S1000-6893.2016.0060

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Off-design performance characteristics of inward turning inlet with rectangular-to-circular shape transition with controlled Mach number distribution

LI Yongzhou1,2, ZHANG Kunyuan1, SUN Di3   

  1. 1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi'an 710100, China;
    3. Xi'an Institute of Aerospace Propulsion Technology, China Aerospace Science and Technology Corporation, Xi'an 710025, China
  • Received:2015-11-02 Revised:2016-03-01 Online:2016-11-15 Published:2016-03-08
  • Supported by:

    National Natural Science Foundation of China (90916029, 91116001)

Abstract:

Based on the axisymmetric basic flowfield of diffusing reflected shock center body with arc tangent Mach number distribution, an inward turning inlet with rectangular-to-circular shape transition is designed. Wind tunnel experiment and numerical simulation are conducted to obtain the off-design performance characteristics and self-starting characteristics. The experimental results indicate that the top wall pressure distribution is of arc tangent curve. The inlet has good overall performance and small vortex region at exit section. For Ma=5.0 and Ma=7.0, the total pressure recovery coefficient of exit section is 0.647 and 0.443, respectively, and the corresponding compression ratio is 20.0 and 32.7, respectively. For Ma=5.0, the inlet could capture about 90% of the free stream and self-start despite its internal contraction ratio being above the Kantrowitz limit; the lower critical back pressure of the inlet is about 64 times of the free stream static pressure, and the corresponding Mach number and total pressure recovery coefficient of exit section are 1.32 and 0.409, respectively. The results demonstrate that high-performance inward turning inlets with rectangular-to-circular shape transition can be designed by the method proposed in this paper.

Key words: inward turning inlets, basic flowfield, Mach number distribution, wind tunnel test, self-starting

CLC Number: