scholarly journals Numerical Investigation on the Reynolds Number Effects of Supercritical Airfoil

2012 ◽  
Vol 31 ◽  
pp. 103-109 ◽  
Author(s):  
Dawei Liu ◽  
Yuanjing Wang ◽  
Dehua Chen ◽  
Xin Peng ◽  
Xing Xu
Keyword(s):  
Reynolds Number ◽  
Numerical Investigation ◽  
Supercritical Airfoil ◽  
Reynolds Number Effects

Numerical investigation of Reynolds number effects on vortex-induced vibrations at low and moderate Re regimes

2022 ◽  
Vol 245 ◽  
pp. 110535
Author(s):  
Jian Gu ◽  
Antonio Carlos Fernandes ◽  
Xiangxi Han ◽  
Xiaofeng Kuang ◽  
Wei Chen
Keyword(s):  
Reynolds Number ◽  
Numerical Investigation ◽  
Vortex Induced Vibrations ◽  
Reynolds Number Effects

Reynolds Number Effect Investigation of Shock Wave on Supercritical Airfoil

2014 ◽  
Vol 548-549 ◽  
pp. 520-524
Author(s):  
Xin Xu ◽  
Da Wei Liu ◽  
De Hua Chen ◽  
Yuan Jing Wang
Keyword(s):  
Shock Wave ◽  
Reynolds Number ◽  
Stokes Equations ◽  
Boundary Layer Separation ◽  
Aerodynamic Characteristics ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Supercritical Airfoil ◽  
Reynolds Number Effects ◽  
Shock Location

The supercritical airfoil has been widely applied to large airplanes for sake of high aerodynamic efficiency. But at transonic speeds, the shock wave on upper surface of supercritical airfoil may induce boundary layer separation, which would change the aerodynamic characteristics. The shock characteristics such as location and intensity are sensitive to Reynolds number. In order to predict aerodynamic characteristics of supercritical airfoil exactly, the Reynolds number effects of shock wave must be investigated.The transonic flows over a typical supercritical airfoil CH were numerically simulated with two-dimensional Navier-Stokes equations, and the numerical method was validated with test results in ETW(European Transonic Windtunnel). The computation attack angles of CH airfoil varied from 0oto 8o, Mach numbers varied from 0.74 to 0.82 while Reynolds numbers varied from 3×106 to 50×106 per airfoil chord. It is obvious that shock location moves afterward and shock intensity strengthens as Reynolds number increasing. The similar curves of shock location and intensity is linear with logarithm of Reynolds number, so that the shock location and intensity at flight condition could be extrapolated from low Reynolds number.

Numerical Investigation on the Reynolds Number Effects of Supercritical Wing

2014 ◽  
Author(s):  
Dawei Liu ◽  
Xin Xu ◽  
Qiang Li ◽  
Mingjie Jiang ◽  
Xin Peng
Keyword(s):  
Reynolds Number ◽  
Numerical Investigation ◽  
Reynolds Number Effects

Reynolds Number Effects on Shock-Wave Turbulent Boundary-Layer Interactions

AIAA Journal ◽  
1977 ◽  
Vol 15 (8) ◽  
pp. 1152-1158 ◽  
Author(s):  
C. C. Horstman ◽  
G. S. Settles ◽  
I. E. Vas ◽  
S. M. Bogdonoff ◽  
C.M. Hung
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Reynolds Number ◽  
Turbulent Boundary Layer ◽  
Reynolds Number Effects
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