THE FLOW
OVER A ROTATING DISC-WING
ARCpaper.pdf(1.9Mb)
Jonathan R. Potts & William J. Crowther
Aerospace Group, School of Mechanical, Aerospace and Civil
Engineering, University of Manchester,
UK
Abstract
An experimental investigation into the
aerodynamics of a rotating disc-wing has
been carried out in an open-circuit wind
tunnel, over a range of Reynolds number
from 1.04*105 to 3.78*105.
The disc-wing considered has an axi-symmetric,
approximately elliptic cross-section and
hollowed out underside cavity. The spin
rate was found to have only a small effect
on the aerodynamic loads but shows some
decrease in rolling moment. The lift and
drag coefficients have been found to be
independent of Reynolds number for the
range of tunnel speeds tested. Observations
from fluorescent paint (flow visualisation)
patterns have revealed the surface flow
regime. The upper surface flow is characterised
by separation at a line (arc) of constant
radius on the leading edge rim, followed
by reattachment at a line of similar geometry.
Trailing vortices detach from the trailing
edge rim. The cavity flow is characterised
by separation at the leading edge lip,
followed by straight-line reattachment.
Reference in Full
Potts J.R. & Crowther W.J., The Flow
Over a Rotating Disc-wing, RAeS Aerodynamics
Research Conference, London, UK, Apr.
2000. |
The following document selection
gives a detailed description of
the research carried out up until
January 2003. The more recent work
is currently being written up and
will be posted as soon as possible. |
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