Redesign of a supercritical wing in the presence of an engine nacelle
A method for modelling an engine nacelle in a compressible flow using a source distribution is described. The incorporation of this technique into a free boundary supercritical wing design code is discussed. Results of calculations made with this code are presented. A method for calculating wave drag is also described.
free boundary supercritical wing design code
scientific article; zbMATH DE number 4027052
scientific article