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Volume 40 Issue 10
Oct.  2014
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Journal of Beijing University of Aeronautics and Astronautics  > 2014  >  40(10): 1341-1348.
Deng Fan, Du Xin, Tan Huijun, et al. Design and validation of cold-flow test for air-breathing hypersonic vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(10): 1341-1348. doi: 10.13700/j.bh.1001-5965.2013.0617(in Chinese)
Citation: Deng Fan, Du Xin, Tan Huijun, et al. Design and validation of cold-flow test for air-breathing hypersonic vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(10): 1341-1348. doi: 10.13700/j.bh.1001-5965.2013.0617(in Chinese)
shu

Design and validation of cold-flow test for air-breathing hypersonic vehicle

doi: 10.13700/j.bh.1001-5965.2013.0617
  • 1.

    Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China

  • 2. Internal Flow Research Center, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

  • 3. The Second Institute, China Academy of Aerospace Aerodynamics, Beijing 100074, China

  • Received Date: 30 Oct 2013
  • Publish Date: 20 Oct 2014
    Abstract
  • Cold-flow test is an important method for air-breathing vehicle to validate the inlet capability and aerodynamic characteristics. An airframe/propulsion integrative cruise vehicle with scramjet egine was designed; two-dimensional mixed-compression inlet and airframe/propulsion system coupling was used. The cold-flow wind tunnel test of the model was finished in hypersonic wind tunnel. Experimental data was measured when free Mach number was 5.0,6.0,7.0, and angle of attack was between -4° and 8°. The pressure performance test results indicate that, with the increase of the free stream Mach number, the total pressure recovery coefficient decreases, while the mass flow ratio increases firstly, and the maximum is obtained at design point; with the range of the angle of attack to a certainty, the total pressure recovery coefficient and the flow ratio increases. But after the cruise angle of attack, with the increase of the angle of attack, the total pressure recovery coefficient and the mass flow ratio decreases. The aerodynamics force performance wind tunnel test results validate the efficiency of the numerical simulation method, which shows a consistent trend with the experimental results, except the axial force coefficient. The aerodynamics characteristics of air-breathing hypersonic cruise vehicle could be obtained by revising the experimental results.

     

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