Article citationsMore>>

Smith, A.N., Babinsky, H., Dhanasekaran, P.C., Savil, A.M. and Dawes, W.N. (2003) Computational Investigation of Groove Controlled Shock Wave/Boundary Layer Interaction. Proceedings of the 41st Aerospace Sciences Meeting and Exhibit, Reno, 6-9 January 2003, AIAA 2003-0446.
http://dx.doi.org/10.2514/6.2003-446

has been cited by the following article:

• TITLE: Control of Transonic Shock Wave Oscillation over a Supercritical Airfoil

  AUTHORS: Muhammad Rizwanur Rahman, Mohammad Itmam Labib, Abul Bashar Mohammad Toufique Hasan, Mohammad Saddam Hossain Joy, Toshiaki Setoguchi, Heuy Dong Kim

  KEYWORDS: Transonic Flow, Shock Oscillation, Passive Control, Airfoil

  JOURNAL NAME: Open Journal of Fluid Dynamics, Vol.5 No.4, December 7, 2015

  ABSTRACT: 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.