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This note summarises the important results
of a detailed experimental investigation into the flow
and pressure distribution over two rectangular single
wedge wings. The experiments were carried out .in the
9" x 9" supersonic tunnel at the College of Aeronautics, 6
at a Mach number of 2.0 and a Reynolds number of 2.5 x 10
per foot. Both wings had a chord of 3 inches and a
total wedge angle of 6°. They had no real trailing
edge, but were faired into a cylindrical support which
could be rolled and pitched in the tunnel. Wing A was
of 2 inch1span, giving an aspect ratio of 0.67. `Ting B
was of 1 1/4 inch span, 0.42 aspect ratio. 132 pressure
tappings 4 were spaced regularly over half of one surface
of each wing, and up to 19 pressure readings could be
taken simultaneously on vertical mercury manometers.
models were pressure plotted at pitch angles of 0°,
2 1/2°, 5°, 7 1/2°, 10°, 15°, 20°, 25°, and 30°, and at all
roll angles at intervals of 30°. Since each wing was
symmetrical about the centreline, the complete pressure
distribution over all surfaces at any roll angle Ø could
he obtained from the readings taken on the one surface
at Ø, 180°- Ø, 180° + Ø, and 360°- Ø. The pressure
readings were then integrated to give the forces and
moments on the complete wing… [cont.]. |
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