The virtual grid method used in the embedding technique to solve the problem of finding interpolating cells of the inner and outer boundary points near joint regions was developed for calculating the viscous flows around a wing with control surface. The main purpose of the virtual grid is to effectively treat the geometry of the crossed facial planes at the interface, and to convert a solid wall boundary condition into an interface condition, however, no fluid flow computations are conducted within the virtual grid. Navier Stokes computations were performed for transonic flow over a clipped delta wing with control surface, and the computed results compare well with the experimental data. The virtual grid method used in the embedding technique to solve the problem of finding interpolating cells of the inner and outer boundary points near joint regions was developed for the calculation of the viscous flows around a wing with control surface. The main purpose of the virtual grid is to effectively treat the geometry of the crossed facial planes at the interface, and to convert a solid wall boundary condition into an interface condition, however, no fluid flow computations were conducted within the virtual grid. Navier Stokes computations were performed for transonic flow over a clipped delta wing with control surface, and the computed results compare well with the experimental data.