A novel method is proposed to predict the delay in boundary layerseparation due to vortex generators (VGs) on two-dimensionalairfoils. The approach is to couple a simple method forpredicting the boundary layer thinning due to VGs with anexisting Euler code (MSES). The objective is to provide a VGdesign tool that is verified by comparison with wind tunnel datafor airfoils near separation. Such a method would shorten theexperimental development process for these devices. It alsooffers the potential to design airfoils which have higher maximumlift at low speeds or higher buffet onset Mach numbers. Theproposed effort is to add equations to the MSES formulation whichaccount for the motion of the vortices near the surface and thecrossflow velocity gradient which thins the boundary layer. Inaddition to verifying the code against wind tunnel data, a VGsystem will be designed to delay the onset of shock inducedseparation on a modern high speed airfoil. The main benefit toNASA and the industry is to provide a tool which enables adesigner to take advantage of the boundary layer control functionof VGs. The method will be extended to multi-element airfoilsand three-dimensional configurations in Phase II.Commercial Applications:Successful completion of the proposed effort will result in improved airfoil technology with direct application to any quasi-two-dimensional subsonic design such as wings, tails, propellers or wind turbines. The gains in maximum lift or Mach number will translate into improved vehicle performance either directly or through better optimized configurations.
