A calculation method for unsteady subsonic flow about harmonically oscillating wing-body configurations

A low-speed aerodynamic model for harmonically oscillating aircraft configurations

“…The non-zero bound vorticity strength at the wing-body junction has been carried over into the fuselage up to its mid-plane. The flow tangency conditions, Equations (6) and 7, are satisfied at the control points lying on wetted surface of the aircraft, shown in Fig. 1 for the fuselage only.…”

“…Another L w collocation points are taken at the wing leading edge. The flow tangency condition, Equations (6) and 7, are satisfied at these collocation points. The Kutta condition of zero loading at the trailing edge gives L w equations thus making exactly N number of equations for N unknown singularity strengths.…”

“…It may be noted that By includes the contribution from the trailing vortices along the edges of the spanwise strips. The normal component of the freestream velocity, b si , is given in Equation(6). oi represents the right hand side of Equation(7) and E lt is the normal component of the complex velocity induced by the vorticity distribution in the wake.…”