Modeling an increase in the lift and aerodynamic efficiency of a thick Göttingen airfoil with optimum arrangement

The Reynolds equations closed using the Menter shear-stress-transfer model modified with allowance for the curvature of flow line have been numerically solved jointly with the energy equation. The obtained solution has been used to calculate subsonic flow (at $\mathrm{M}$ = 0.05 and 5$^\circ$ angle of attack) past a thick (24% chord) Göttingen airfoil with variable arrangement of a small-sized (about 10% chord) circular vortex cell with fixed distributed suction $C_q$ = 0.007 from the surface of a central body. It is established that the optimum arrangement of the vortex cell provides a twofold decrease in the bow drag coefficient $C_x$, a threefold increase in the lift coefficient $C_y$, and an about fivefold increase in the aerodynamic efficiency at Re = 10$^5$ in comparison to the smooth airfoil.