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Advances in Aircraft and Spacecraft Science
  Volume 1, Number 4, October 2014, pages 443-454
DOI: http://dx.doi.org/10.12989/aas.2014.1.4.443
 


Effect of Reynolds number on compressible convex-corner flows
Kung-Ming Chung, Po-Hsiung Chang and Keh-Chin Chang

 
Abstract
    An experimental study was conducted to investigate the effect of Reynolds number on compressible convex-corner flows, which correspond to an upper surface of a deflected flap of an aircraft wing. The flow is naturally developed along a flat plate with two different lengths, resulting in different incoming boundary layer thicknesses or Reynolds numbers. It is found that boundary layer Reynolds number, ranging from 8.04x104 to 1.63x105, has a minor influence on flow expansion and compression near the corner apex in the transonic flow regime, but not for the subsonic expansion flow. For shock-induced separated flow, higher peak pressure fluctuations are observed at smaller Reynolds number, corresponding to the excursion phenomena and the shorter region of shock-induced boundary layer separation. An explicit correlation of separation length with deflection angle is also presented.
 
Key Words
    convex corner; Reynolds number; shock; pressure fluctuations; boundary layer separation
 
Address
Kung-Ming Chung : Aerospace Science and Technology Research Center, National Cheng Kung University, 2500 Section 1, Chung-Cheng South Road, Guiren district, Tainan, 711, Taiwan
Po-Hsiung Chang and Keh-Chin Chang : Department of Aeronautics and Astronautics, National Cheng Kung University, 1 University Road, East district, Tainan, 701, Taiwan
 

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