A preliminary technique has been developed for the design of wings to be used with supersonic hybrid method laminar flow control systems. This technique has been used to evaluate the effects on aerodynamic performance of designing supersonic wings for laminar flow control. In this design method, a wing is cambered such that it produces an upper-surface streamwise pressure distribution which is favorable for use in a hybrid laminar flow control (HLFC) system, while maintaining a spanwise lifting distribution which will minimize drag-due-to-lift. An existing linear-theory computer program is used to calculate the wing camber definition that produces a desired pressure distribution on the upper surface of the wing with a specified thickness profile. This method was applied to an array of arrow-wings varying in aspect ratio and taper ratio. Each wing planform was then camber-optimized for minimum cruise drag-due-to-lift using current preliminary wing design methods, which optimize the wing's camber of lifting load distribution without regard to the boundary layer type.
Effects on aerodynamic performance of designing supersonic wings for laminar flow control
Einfluß der Konstruktion von Überschalltragflächen zur Aufrechterhaltung laminarer Strömungsverhältnisse auf die aerodynamischen Eigenschaften
US Government Reports ; Jan ; 1-90
1991
90 Seiten
Report
English
Design-Oriented Aerodynamic Analysis for Supersonic Laminar Flow Wings
British Library Conference Proceedings | 2003
|1125-1155 Aerodynamic Design of Natural Laminar Flow Supersonic Aircraft Wings
British Library Conference Proceedings | 2000
|Aerodynamic Optimization of Supersonic Wings
NTIS | 1983
|