Abstract:

ESDU Aero F.02.01.08 derives the vortex drag coefficient, in incompressible flow, of an isolated wing with symmetrically-deployed multiple part-span flaps and a central cut-out. The method is restricted by the simplifying assumptions that the wing without deployed flaps is taken to have an elliptical spanwise loading and that flap deployment is assumed to take place without chord extension. ESDU 97002 discusses other forms for the trailing vortex drag when these simplifying assumptions do not apply. For the case when a fuselage is present in the central cut-out between the inboard ends of the inner-most flap panels, ESDU 97003 gives a method to allow for the interference effect between the flaps and the fuselage.

Format: PDF, with software.