Vortex Cell with a Cylinder Rotating inside it on the Surface of an Airfoil Section at High Reynolds Numbers

An algorithm for eliminating flow separation in the nose region of a symmetric airfoil section at nonzero angle of incidence is proposed. Below the separation-prone region of the section, to increase the critical angle of incidence, a vortex cell with a cylinder rotating inside is located. The shape of the vortex cell and the precise location of the cylinder are so chosen as to create the same pressure gradient in the mixing layer as in the external flow.