Active Control of Forebody Vortices on a schematic Aircraft Model
Abstract
A wind-tunnel experiment has been performed to further investigate the potential of the dynamic manipulation of forebody vortices as a means of supplementing directional control of fighter aircraft at high angles of attack. Tests wore conducted On a 65-deg delta-wing model fitted with a slender, pointed tangent-ogive focebody of circular cross- section. Forward-blowing nozzles located near the apex of the forebody served as the means of perturbing the forebody vortices. Results have shown that a linear relationship exists between the time-average yawing moment coefficient and a duty cycle parameter. These results, however, are accompanied by a peculiar reversal of yawing moment and side force that occurs when the blowing momentum exceeds a particular threshold value. Cross-coupling effects were also identified between the control method and time-average rolling moment, pitching moment, and normal force.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2001
- Accession Number
- ADP011119
Entities
People
- E. S. Hauff
- R. J. Kind
- R. Lee
Organizations
- Carleton University