导航

ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2016, Vol. 37 ›› Issue (10): 2970-2979.doi: 10.7527/S1000-6893.2016.0035

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Experimental investigation on a hypersonic inward turning inlet of rectangular-to-circular shape 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:2015-10-13 Revised:2015-12-28 Online:2016-10-15 Published:2016-02-22
  • Supported by:

    National Natural Science Foundation of China (90916029, 91116001)

Abstract:

Based on the axisymmetric basic flowfield with diffusing reflected shock center body and arc tangent Mach number distribution, an inward turning inlet with rectangular-to-circular transition is designed. The experiment on the wind tunnel and numerical simulation are conducted to obtain the operation characteristics of the design point. The experimental results indicate that the pressure distribution of the top wall is characterized by an arc tangent curve. The inlet is of good overall performance, and the vortex region is small. In conclusion, the design method proposed is feasible and efficient. For the design point, the total pressure recovery coefficient is 0.561 and the compression ratio is 26.2 at the exit section. The critical back pressure is about 135 times of the free stream static pressure, and the corresponding total pressure recovery coefficient is 0.210. With 4°attack angle, the compression ratio increases by 49.6% but the total pressure recovery coefficient decreases by 17.5% at the exit section.

Key words: inward turning inlets, basic flowfield, Mach number distribution, wind tunnel test, shape transition

CLC Number: