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Impinging jets in cross-flow

Published online by Cambridge University Press:  04 July 2016

K. Knowles ,
D. Bray ,
P. J. Bailey  and
P. Curtis
K. Knowles
Affiliation:
Aeromechanical Systems Group Royal Military College of Science
D. Bray
Affiliation:
Aeromechanical Systems Group Royal Military College of Science
P. J. Bailey
Affiliation:
Logico Systems Ltd East Horsley
P. Curtis
Affiliation:
Aerodynamics DepartmentBritish Aerospace Military Aircraft LtdKingston-upon-Thames
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Abstract

The flow-fields associated with single and twin jets impinging in cross-flows have been studied. Parameters which affect the position of the ground vortex have been investigated: cross-flow-to-nozzle velocity ratio, cross-flow boundary layer thickness, nozzle height, nozzle pressure ratio, vector angle and nozzle splay with both fixed and moving ground planes. Results show that the ground vortex moves away from the nozzle centre-line as the ratio of cross-flow velocity to nozzle exit velocity is decreased; the rate of change of position, however, depends on other parameters (including the precise definition of nozzle exit velocity). Increasing nozzle height above the ground appears to cause little consistent variation in vortex position for a single jet but a marked forward movement of ground sheet separation point in the case of twin jets. For all cases there is an increase in penetration with increasing nozzle pressure ratio up to choking, with the subsequent behaviour dependent on the definition of nozzle equivalent velocity and cross-flow velocity ratio. The effect of the moving ground plane is to reduce vortex penetration significantly; this suggests that a moving ground plane simulation (or moving model) is essential when testing design configurations in ground effect in wind-tunnels. It is also shown that rig design can produce a blockage effect which moves the ground vortex significantly and can change other apparent parametric effects. Self-similarity laws are proposed for the ground vortex and the wall jet.

Type
Research Article
Information
The Aeronautical Journal , Volume 96 , Issue 952 , February 1992 , pp. 47 - 56
Copyright
Copyright © Royal Aeronautical Society 1992 

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