The Transonic Multifoil Augmentor Wing

Abstract

The paper describes the development of a thick (f/c = 0.18) transonic, multifoil, blown augmentor-wing section and discusses the results of a series of wind-tunnel tests on the configuration. The results show that the blown multifoil section enjoys two advantages over a conventional unblown single-foil supercritical section of the same overall thickness-chord ratio: 1) "effective" drag reduced by blowing, and 2) increased drag rise Mach number (M D = 0.75); they also demonstrate that augmentor blowing improves the buffet boundaries of the section. Thus, overall, it has been shown that the augmentor flap configuration is capable of extending the speed range of a jet transport aircraft to the very low approach speeds required by STOL aircraft [as demonstrated by the NASA/DITC (Canadian Department of Industry Trade and Commerce) augmentor-wing STOL research aircraft] and also to the high subsonic speed required for cruise, where it is shown to be competitive with the plain supercritical airfoil.

Computational Investigation of Two-Dimensional Ejector Performance

“…In effect, an ejector functions like a ducted fan in which jet entrainment provides the pumping action of the fan. The measure of ejector performance is the thrust augmentation ratio (Φ) which is the ratio of the total Ejector thrust augmentation provides a solution to many of the problems associated with developing STOVL aircraft [3][4][5][6][7] . In particular, the additional thrust required for vertical takeoffs and landings can be obtained from a smaller engine sized for efficient mission performance.…”