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YUAN Chao-kai, SUN Ying-ying, JIANG Zong-lin. Free Flight Test in Hypersonic Impulse Wind Tunnel[J]. PHYSICS OF GASES, 2016, 1(2): 55-63.
Citation: YUAN Chao-kai, SUN Ying-ying, JIANG Zong-lin. Free Flight Test in Hypersonic Impulse Wind Tunnel[J]. PHYSICS OF GASES, 2016, 1(2): 55-63.
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Free Flight Test in Hypersonic Impulse Wind Tunnel

  • Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, CAS, Beijing 100190, China

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  • Received Date: December 02, 2015
  • Revised Date: December 14, 2015
  • Published Date: March 19, 2016
    Graphical Abstract
    • Abstract
  • Free flight test can obtain aerodynamic parameters using the model's motion trajectory, which was recorded by high speed camera. It has unique advantages in the study of aircraft dynamic/static stability for its characters of no support system because of its true simulation of the flight condition. A free flight test was carried out in the JF-8A hypersonic wind tunnel with a 10°cone model, simultaneously, a ball model was used to measure the dynamic pressure. In this paper, the key method of extracting motion parameters and aerodynamic characters were also introduced in detail.
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    • References (14)
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