Aerodynamic design of transonic wings using the target pressure optimization approach

A target pressure optimization code with a genetic algorithm was developed for the inverse design of transonic wings. The shock strength was minimized, and the isobar line sweep angles on the upper surface of the wing were maximized to obtain minimum wave drag while constraints on spanwise lift distribution and section pitching moments were satisfied. With the target pressures at each design section specified, an inverse design code was run subsequently to obtain the wing geometry. The designed wing showed better performance than the baseline wing at the given design condition, and geometrical constraints on the section contour area are successfully satisfied. Design results show that the inverse design using the target pressure optimization approach was very efficient in obtaining a transonic wing of high performance at a given design condition.