Numerical Investigation on Shock-Induced Separation Structure of Supercritical Airfoil

Xin Xu; Da Wei  Liu; De Hua Chen; Yuan Jing Wang

doi:10.4028/www.scientific.net/AMR.756-759.4502

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 756-759Numerical Investigation on Shock-Induced...

Numerical Investigation on Shock-Induced Separation Structure of Supercritical Airfoil

Abstract:

The supercritical airfoil has been widely applied to large airplanes for sake of high aerodynamic efficiency. But at transonic speeds, the complicated shock-induced separation on the upper surface of supercritical airfoil will change the aerodynamic characteristics. The transonic flows over a typical supercritical airfoil CH were numerically investigated in this paper, in order to analyses different shock-induced separation structure. The two-dimensional Navier-Stokes equations were solved with structure grids by utilizing the S-A turbulence model. The computation attack angles of CH airfoil varied from 0oto 4o, Mach numbers varied from 0.74 to 0.82 while Reynolds numbers varied from 3×10⁶ to 50×10⁶ per airfoil chord. It is shown that with the attack angle increases, the separation bubble occurred on the upper surface first, then the trailing-edge separation occurred, the trailing-edge would separate totally at last. The different separation structure would result in different pressure coefficient distribution and boundary layer thickness.

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Periodical:

Advanced Materials Research (Volumes 756-759)

Pages:

4502-4505

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.756-759.4502

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Online since:

September 2013

Authors:

Xin Xu, Da Wei Liu, De Hua Chen, Yuan Jing Wang

Keywords:

N-S Equations, Numerical Investigation, Shock-Induced Separation, Supercritical Airfoil

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