Control of Transonic Shock Wave Oscillation over a Supercritical Airfoil

Muhammad Rizwanur Rahman, Mohammad Itmam Labib, Abul Bashar Mohammad Toufique Hasan, Mohammad Saddam Hossain Joy, Toshiaki Setoguchi, Heuy Dong Kim
2015 Open Journal of Fluid Dynamics  
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
more » ... rodynamic 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.
doi:10.4236/ojfd.2015.54031 fatcat:xkwzdkwbjzektgygkococpxbve