Progress 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.
A direct-inverse transonic wing-design method in curvilinear coordinates including viscous-interaction
AIAA Applied Aerodynamics Conference ; 1989 ; Seattle, WA, United States
01.01.1989
Aufsatz (Konferenz)
Keine Angabe
Englisch