Control of Transonic Shock Wave Oscillation over a Supercritical Airfoil
<|begin_of_text|><|start_header_id|>system<|end_header_id|> You are a research archivist expert in dataset metadata. Answer the question truthfully.  <|eot_id|><|start_header_id|>user<|end_header_id|> Here is the Description of a dataset. Description:'In the present study, a numerical investigation is carried out on the aerodynamic performance of asupercritical airfoil RAE 2822. Transonic flow fields are considered where self-excited shock waveoscillation prevails. To control the shock oscillation, a passive technique in the form of an openrectangular 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 aerodynamicbehavior of the baseline airfoil and airfoil with cavity at Mach number of 0.729 and at angle of attackof 5˚. The aerodynamic characteristics of the baseline airfoil are well validated with theavailable experimental data. It is observed that the introduction of a cavity around the airfoil uppersurface can completely stop the self-excited shock w' . Please return only a json list of at most 3 Keywords corresponding to the Description:.<|eot_id|><|start_header_id|>assistant<|end_header_id|> {"Answer" : ["shock oscillation, transonic, supercritical, airfoil"]} <|eot_id|>
 Here is the Description of a dataset. Description:'In the present study, a numerical investigation is carried out on the aerodynamic performance of asupercritical airfoil RAE 2822. Transonic flow fields are considered where self-excited shock waveoscillation prevails. To control the shock oscillation, a passive technique in the form of an openrectangular 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 aerodynamicbehavior of the baseline airfoil and airfoil with cavity at Mach number of 0.729 and at angle of attackof 5˚. The aerodynamic characteristics of the baseline airfoil are well validated with theavailable experimental data. It is observed that the introduction of a cavity around the airfoil uppersurface can completely stop the self-excited shock w' . Please return only a json list of at most 3 Keywords corresponding to the Description:.
In the present study, a numerical investigation is carried out on the aerodynamic performance of asupercritical airfoil RAE 2822. Transonic flow fields are considered where self-excited shock waveoscillation prevails. To control the shock oscillation, a passive technique in the form of an openrectangular 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 aerodynamicbehavior of the baseline airfoil and airfoil with cavity at Mach number of 0.729 and at angle of attackof 5˚. The aerodynamic characteristics of the baseline airfoil are well validated with theavailable experimental data. It is observed that the introduction of a cavity around the airfoil uppersurface can completely stop the self-excited shock w
shock oscillation, transonic, supercritical, airfoil