The influence of deviation of the trailing edge of supercritical wing airfoil McDonnell/Douglas DSMA-523 in the range of Mach numbers 0,48 M 0,95 and angles of attack –10 10 , with Reynolds numbers Re 106 has been investigated. It is shown that the deviation of the trailing edge of airfoil up can increase the critical Mach number. The deviation of the trailing edge of the airfoil down allows one to increase an aerodynamic efficiency. Practical recommendations for the use deviation of the trailing edge of the airfoil on existing aircrafts have been given.
supercritical airfoil, Mach number, angle of attack, lift coefficient, drag coefficient, trailing edge