A direct-inverse transonic wing-design method in curvilinear coordinates including viscous-interactionProgress in the direct-inverse wing design method in curvilinear coordinates has been made. A spanwise oscillation problem and proposed remedies are discussed. Test cases are presented which reveal the approximate limits on the wing's aspect ratio and leading edge wing sweep angle for a successful design, and which show the significance of spanwise grid skewness, grid refinement, viscous interaction, the initial airfoil section and Mach number-pressure distribution compatibility on the final design. Furthermore, preliminary results are shown which indicate that it is feasible to successfully design a region of the wing which begins aft of the leading edge and terminates prior to the trailing edge.
Document ID
19890060292
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ratcliff, Robert R. (Texas A&M Univ. College Station, TX, United States)
Carlson, Leland A. (Texas A & M University College Station, United States)