A wind tunnel test was conducted to determine the effects of over-the-wing blowing as a means of augmenting the leading-edge vortex flow of several pointed-tip, sharp-edged planforms. Arrow, delta, and diamond wings with leading-edge sweeps of 30 and 45 degrees were mounted on a body-of-revolution fuselage and tested in a low-speed wind tunnel at a Mach number of 0.2. Nozzle location data, pitch data, and flow-visualization pictures were obtained for a range of blowing rates. Results show pronounced increases in vortex lift due to the blowing.
An experimental investigation of leading-edge vortex augmentation by blowing
1974-04-01
Report
Keine Angabe
Englisch
Leading-edge-vortex augmentation in compressible flow
AIAA | 1975
|Leading-Edge-Vortex Augmentation in Compressible Flow
AIAA | 1976
|Control of leading edge vortex breakdown by blowing
AIAA | 1988
|