Chigrin R. A method of determination of a discoid wing with wing-tip airfoils aerodynamic characteristics in wide range of angle of attack variation.

Dissertation is devoted to the rational geometrical parameters of end airfoils basis that provide a discoid wing with maximal aerodynamic lift/drag ratio, taking into account features of influence by leading edge vortex in wide range of angle of attack variation. The low order panel method that uses different models of calculation of influence coefficients from simple and double layers potentials is improved. Regularities of change in discoid wing total aerodynamic characteristics with geometrical parameters of wing-tip airfoils in wide range of angles of attack are set, which show possibility of trailing overflow diminishing and decreasing of a stall on large angles of attack. Recommendations of rational sampling of geometrical parameters of a discoid wing with wing-tip airfoils aerodynamic compound to provide maximum number of lift/drag ratio are established.