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Control of Transonic Shock Wave Oscillation over a Supercritical Airfoil

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DOI: 10.4236/ojfd.2015.54031    4,320 Downloads   5,005 Views   Citations


In the present study, a numerical investigation is carried out on the aerodynamic performance of a supercritical airfoil RAE 2822. Transonic flow fields are considered where self-excited shock wave oscillation prevails. To control the shock oscillation, a passive technique in the form of an open rectangular cavity is introduced on the upper surface of the airfoil where the shock wave oscillates. Reynolds Averaged Navier-Stokes (RANS) equations have been used to predict the aerodynamic behavior of the baseline airfoil and airfoil with cavity at Mach number of 0.729 and at angle of attack of 5°. The aerodynamic characteristics of the baseline airfoil are well validated with the available experimental data. It is observed that the introduction of a cavity around the airfoil upper surface can completely stop the self-excited shock wave oscillation and successively improve the aerodynamic characteristics.

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Rahman, M. , Labib, M. , Hasan, A. , Joy, M. , Setoguchi, T. and Kim, H. (2015) Control of Transonic Shock Wave Oscillation over a Supercritical Airfoil. Open Journal of Fluid Dynamics, 5, 302-310. doi: 10.4236/ojfd.2015.54031.

Conflicts of Interest

The authors declare no conflicts of interest.


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