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Yaw control by tangential forebody blowing

Published online by Cambridge University Press:  04 July 2016

N.J. Wood  and
W.J. Crowther
N.J. Wood
Affiliation:
School of Mechanical Engineering University of Bath
W.J. Crowther
Affiliation:
School of Mechanical Engineering University of Bath
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Summary

Aircraft yaw control at high angles of attack by tangential forebody blowing has been investigated experimentally. Tests were performed in the University of Bath 21 m x 1.5 m low speed wind tunnel using a 6% scale generic combat aircraft model fitted with blowing slots in the nose cone. Six component strain gauge balance force and moment data were measured for angles of attack up to 90° for various slot geometries and locations. The effect of slot azimuthal location is demonstrated and a slot stall phenomenon described. A geometry dependent forebody/wing flowfield coupling has been identified which can lead to unexpected yawing and rolling moments. The primary source of yawing moment is shown to be the enhanced area of attached flow on the blown side of the forebody rather than direct vortex influence.

The optimum slot extent and location depend on the angle of attack range over which control is required. For regions where steady vortex asymmetry is present, slots near the apex of the forebody produce severe control reversals at low blowing rates. These reversals can be minimised by placing the slots away from the apex. For control in regions where the flow is dominated by periodic vortex shedding, long slots offer efficient control to 90° angle of attack. The most suitable compromise for wide range control would appear to be a short slot placed away from the apex of the forebody.

Type
Research Article
Information
The Aeronautical Journal , Volume 98 , Issue 974 , April 1994 , pp. 147 - 154
Copyright
Copyright © Royal Aeronautical Society 1994 

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