Calculation of Aerodynamic Characteristics on Delta Wing with Leading-Edge Separation Vortex Effect Using Boundary Element Method

摘要

In this paper, a method which allows the calculation of the characteristics for a flow around a delta wing is described. Flow separations are certain to occur from the leading-edge on highly swept wings at moderate to high angles of attack. Since a delta wing is considered to be a slender body, slender body theory is employed. The slender body theory assumes that the flow is composed of an axial flow and a cross flow. At first, two-dimensional cross sections are generated by slicing a three-dimensional model and the position and strength of leading-edge separation vortices are determined using the vortex tracking method. In order to include the effect of leading-edge separation vortex, a model is proposed. Some aerodynamic coefficients of a delta wing are obtained from the present method. Comparisons between numerical and experimental results show good agreement.