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He Yuanyuan, Wu Yingchuan, Zhang Xiaoqing, Lin Qi. Analysis of data correlation between combustion heated impulse facility and hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(3): 64-68. DOI: 10.11729/syltlx20180011
Citation: He Yuanyuan, Wu Yingchuan, Zhang Xiaoqing, Lin Qi. Analysis of data correlation between combustion heated impulse facility and hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(3): 64-68. DOI: 10.11729/syltlx20180011
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Analysis of data correlation between combustion heated impulse facility and hypersonic wind tunnel

  • Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

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  • Received Date: January 17, 2018
  • Revised Date: May 12, 2018
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    • Abstract
  • The simulation parameters of different hypersonic test facilities have large influence to the test results. A typical lift body aerodynamic test was conducted in the combustion heated impulse facility and hypersonic wind tunnel. The influence of Reynolds number and wall temperature ratio was analyzed. The aerodynamic changes of the combustion heated impulse facility test were in consistence with those of the hypersonic wind tunnel test, but its drag coefficients were about 15% larger. Numerical analysis indicates that the differences caused by Reynolds number were about 5%, and those caused by the wall temperature ratio were about 10%, and therefore the change of velocity boundary layer is the main factor.
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    • References (15)
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