Shock-Boundary Layer Interaction Control,Predictions Using a Viscous-Inviscid Interaction Procedure and a Navier-Stokes Solver  

作　　者：G. Simandirakis  B. Bouras K.D. Papailiou (National Technical University of Athens, Laboratory of Thermal Turbomachines, P.O. Box 64069,157 10 Athens, Creece) 

出　　处：《Journal of Thermal Science》1997年第2期97-110,共14页热科学学报（英文版）

摘　　要：The present contribution describes two prediction methods for flows around transonic airfoils, including shock control devices. The wliole work was done in the frame of the European Shock Control Inves tigation Project EUROSHOCK-AER-2, and the global objective was the improvement of the flight performance, in transonic speed, in terms of cruise speed, fuel consumption and exhaust emissions for both laminar and turbulent wings. More specilically the "passive" control of shock/boundary layer interaction, whereby part of the solid suLrfaCe of the airfoil is replaced by a porous surface over a shallow cavity, has been shown to be a means of improving the aerodynamic characteristics of supercritical airfoils.

关 键 词：shock/boundary layer interaction passive control transonic airfoils 

分 类 号：O357.4[理学—流体力学]