Zaharenko V. The determination method of aerodynamic characteristics of thin airfoil of high-altitude subsonic aircrafts at large angles of attack

The object is the flow round a thin airfoil with flow separation at large angles of attack. The aim is development of method of determination of aerodynamic characteristics of thin high-altitude subsonic aircraft's airfoils at large angles of attack. The methods are the method of boundary integral equations and the method of singularities. The novelty is that for a first time the method of determination of aerodynamic characteristics of thin airfoils at large angles of attack with flow separation in which the boundary conditions, which are differed from existing is proposed and based on the theory of ideal liquid; mathematic model in which as a closure equations the boundary conditions on tips of airfoil are used that required the providing of velocity finiteness in that points.The results are the essentiall decreasing of time of airfoil aerodynamic characteristics calculation in the aircraft design phase. The branch is aircraft construction.