Kaleniuk I. Adaptation of the wing with supercritical airfoil for improving its aerodynamic characteristics

object: flow over the supercritical airfoil and the finite span wing at high subsonic speeds; objective: improving the aerodynamic characteristics and increasing the critical Mach number of the wing of cruise flight with supercritical airfoil by adapting it to the flow regime; methods: methods for the numerical simulation of flow near supercritical airfoils and finite span wing by solving system of the Reynolds-averaged Navier – Stokes equations; results: an approach for adaptation of the wing to its flow regime at high subsonic speeds was suggested; novelty: for the first time a technical solution that consists of an adaptive to the flight regime change in the airfoil shape near the trailing edge, that provides multi-mode capabilities for finite span wing with supercritical airfoil is proposed; for the first time the relationship between the geometric parameters, the aerodynamic characteristics and the critical Mach number on the basis of complex multi-parameter numerical studies of supercritical airfoils and their modifications near the trailing edge is obtained; for the first time the effect of the up deviation of the trailing edge of the supercritical airfoil and finite span wing on their aerodynamic characteristics and the coefficient of aerodynamic efficiency is numerically determined; field: aircraft construction.