A numerical simulation of flow around of the supercritical airfoil of the second generation McDonnell/Douglas DSMA-523 with a sharp and a modified trailing edge in the transonic speed range and a wide range of angles of attack was done. Modification of the shape of the airfoil consisted in changing the upper (lower, both) of the surface to thickening of the trailing edge of airfoil by an amount of 0,5 to 2% chord length. The analysis of the impact of change in the shape of a supercritical airfoil on its basic aerodynamic characteristics was made.
supercritical airfoil, Mach number, angle of attack, lift coefficient, drag coefficient, modification of the surface of airfoil, trailing edge
"Chyslennoe modelyrovanye obtekanyia sverkhkrytycheskoho profylia s modyfytsyrovannoi verkhnei (nyzhnei) poverkhnostiu" ,
Scientific Works of Kharkiv National Air Force University,