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International journal of heat and mass transfer v.121, 2018년, pp.986 - 998   SCI SCIE
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Numerical simulation of local wall heating and cooling effect on the stability of a hypersonic boundary layer

Zhao, R.    (School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China   ); Wen, C.Y.    (Department of Mechanical Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong Special Administrative Region   ); Tian, X.D.    (Department of Mechanical Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong Special Administrative Region   ); Long, T.H.    (Department of Mechanical Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong Special Administrative Region   ); Yuan, W.    (Supercomputing Center, Computer Network Information Center, Chinese Academy of Sciences, Beijing 100190, China  );
  • 초록  

    Abstract In this study, a numerical investigation of the perturbation evolution in a Mach 6 flat-plate boundary layer with a local heating or cooling strip is presented. The position of the temperature strip is varied while the strip length is constant and approximated to the boundary-layer thickness. Simulations are based on a time-accurate integration of the compressible Navier-Stokes equations, with a small disturbance of fixed frequency triggered via periodic suction-blowing at the plate leading edge. The stability characteristics of the hypersonic boundary layer are interpreted by spatial linear stability theory (LST). The results indicate that the relative location of a local heating/cooling strip and the synchronization point significantly affect Mode S . With respect to the heating-strip cases, the unstable mode is amplified when a heating strip is located upstream of the synchronization point, and the effect is reversed if the heating strip is placed downstream. In a manner opposite to the local heating effect, placing a narrow cooling strip upstream of the synchronization point stabilizes mode S , while the effect is reversed if the cooling strip is put downstream of the synchronization point. Different from previous stability studies on roughness and porous wall, the location of the synchronization point is not fixed, and this is mainly caused by the change to the phase speed of Mode F . The results suggest that an efficient way to stabilize the boundary layer is to put a narrow cooling strip further upstream of the synchronization point, or put a narrow heating strip downstream of the synchronization point. Highlights The relative location of a temperature strip and the syn. point affect Mode S . The location of the syn. point is changed due to the phase speed change of Mode F . Put a narrow cooling strip upstream of the syn. point could stabilize the BL. Put a narrow heating strip downstream of the syn. point could stabilize the BL.


  • 주제어

    Hypersonic boundary layer .   Boundary layer transition .   Laminar flow control .   Temperature strip.  

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