Lifting line theory for supersonic flow applications
We are devoted to the study of a supersonic lifting line theory intended to provide both a means of aerodynamic calculation and a benchmark for the validation of the control point position for the related constant pressure panel methods. The model is based on the small perturbations assumption. A constant distribution of bound vortices is assumed along the chord whereas the spanwise load distribution is by means of trigonometrical series, formally similar to the subsonic methods.