Compressibility effect in hypersonic boundary layer with isothermal wall condition

2021 ◽  
Vol 6 (5) ◽  
Author(s):  
Dehao Xu ◽  
Jianchun Wang ◽  
Minping Wan ◽  
Changping Yu ◽  
Xinliang Li ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Hypersonic Boundary Layer ◽  
Compressibility Effect ◽  
Wall Condition ◽  
Isothermal Wall

Large Eddy Simulations of Separated Boundary Layer With Pressure Gradient and Heat Transfer

2018 ◽  
Author(s):  
Yifei Wu ◽  
Weihao Zhang ◽  
Zhengping Zou ◽  
Jiang Chen
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Large Scale ◽  
Separation Bubble ◽  
Bottom Wall ◽  
Wall Heat Transfer ◽  
Adiabatic Wall ◽  
Wall Condition ◽  
Spanwise Vortex ◽  
Isothermal Wall

Separated boundary layers of the low pressure turbine blade suction surface under wall heat transfer and pressure gradient conditions are investigated using large eddy simulations (LES) in this paper. The study constructed a converging-diverging channel with a flat plate as the bottom wall, and the pressure distribution of the bottom wall is similar to that of a high lift low pressure turbine blade suction surface. The boundary layer was investigated under different heat transfer boundary conditions of the bottom wall (i.e., the adiabatic wall and the isothermal wall with the wall temperature being 0.8 times of the inflow temperature). The time-averaged flow parameters and the separation bubble characteristics were analyzed and discussed. The evolution of coherent structure diagrams of the boundary layer was also obtained to study the evolution process of the vortex. The results show that the cooled isothermal wall condition can significantly suppress the separation bubble and reduce the frequency of the large scale spanwise vortex roll-up. Under the two wall heat transfer conditions, the scale of the near wall small scale spanwise vortex is similar as well as the scale of the large scale spanwise wortex. The location of the vortex are also approximate under the two wall heat transfer conditions, but the position of the large scale spanwise vortex shedding from separated laminar boundary layers moves upstream under the cooled isothermal wall condition, and the transition process is more rapid than that of the adiabatic wall condition.

Effect of angle of attack on hypersonic boundary-layer stability

AIAA Journal ◽  
1997 ◽  
Vol 35 ◽  
pp. 464-470 ◽  
Author(s):  
Glen P. Doggett ◽  
Ndaona Chokani ◽  
Stephen P. Wilkinson
Keyword(s):  
Boundary Layer ◽  
Angle Of Attack ◽  
Boundary Layer Stability ◽  
Hypersonic Boundary Layer

scholarly journals Shock-induced heating and transition to turbulence in a hypersonic boundary layer

2020 ◽  
Vol 909 ◽  
Author(s):  
Lin Fu ◽  
Michael Karp ◽  
Sanjeeb T. Bose ◽  
Parviz Moin ◽  
Javier Urzay
Keyword(s):  
Boundary Layer ◽  
Transition To Turbulence ◽  
Hypersonic Boundary Layer

Abstract

scholarly journals Nonlinear interactions in a hypersonic boundary layer

AIP Advances ◽  
2021 ◽  
Vol 11 (3) ◽  
pp. 035104
Author(s):  
Chuanhong Zhang ◽  
Zhiwei Shi
Keyword(s):  
Boundary Layer ◽  
Hypersonic Boundary Layer ◽  
Nonlinear Interactions

scholarly journals Investigation on the depth effects of the micro-grooves on the suppression of the second modes in the hypersonic boundary layer

2021 ◽  
Vol 1786 (1) ◽  
pp. 012053
Author(s):  
Qilong Guo ◽  
Chen Li ◽  
Guohua Tu ◽  
Jianqiang Chen ◽  
Bingbing Wan ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Hypersonic Boundary Layer ◽  
Depth Effects
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