A method of modifying the upper/lower surface of the supercritical airfoil at the trailing edge area that will improve its aerodynamic characteristics and bearing properties has been proposed. The numerical simulation of the supercritical airfoil McDonnell/Douglas DSMA-523 and its modifications has been done by solving the RANS equations. It is shown that the rise of trailing edge up by reducing the curvature of the surface profile increases the critical Mach number, and the lowering of the trailing edge down leads to an increase aerodynamic efficiency by increasing the curvature of the mean line of the airfoil near the trailing edge.
supercritical airfoil, modification, critical Mach number, angle of attack, lift coefficient, drag coefficient, lift to drag ratio
"Metod modyfykatsyy sverkhkrytycheskoho profylia v oblasty zadnei kromky" ,
Science and Technology of the Air Force of Ukraine,