Abstract: An aircraft including a fuselage, a compound tilting wing (CTW) and aircraft engines mounted on the aircraft. The CTW includes a leading edge wing portion and a tilting main wing portion. The leading edge wing portion and the tilting main wing portion each include a leading edge, a trailing edge, a chord, a lower surface and an upper surface. The tilting main wing portion is pivotally mounted on the fuselage for rotation from a cruise flight position to various low flight speed positions. In the cruise flight position, the tilting main wing portion fits conformably with the leading edge wing portion forming an aerodynamically single wing. In one embodiment, two aircraft engines are mounted on a fixed leading edge wing portion and two aircraft engines are mounted on the tilting main wing portion.

Abstract: Aerodynamic performance parameters for aircraft configurations are calculated using an aerodynamic performance system and method. The aerodynamic performance system in a workstation includes a processor circuit having a processor and a memory. Additionally, the system includes aerodynamic performance logic stored on the memory and executable by the processor. The aerodynamic performance logic includes logic that calculates a number of aerodynamic performance parameters for a configuration. Further, the logic generates an aerodynamic performance report to be sent to a client via a network. The aerodynamic performance report lists at least one of the aerodynamic performance parameters.