Abstract:
A numerical method of solving the integral equation connecting the lift and downwash on a wing oscillating harmonically in a supersonic flow of any Mach number is described. The integral equation is replaced by a matrix equation connecting the values of the lift and downwash at sets of points on the wing, and the generalised aerodynamic forces acting on the wing are found simply as a matrix product. Comparisons are made between aerodynamic derivatives calculated by this method, and theoretical and experimental derivatives from other sources.
