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A Wind Tunnel Investigation of a Thin Aerofoil with a Sharp Leading Edge, and Blowing Applied at the Mid-Chord at Two Angles Relative to the Surface

Published online by Cambridge University Press:  04 July 2016

I. Wygnanski
I. Wygnanski*
Affiliation:
formerly Mechanical Engineering Research Laboratories, Mc Gill University, now Boeing Scientific Research Laboratories, Seattle
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Summary

Experiments have been made on a thin two-dimensional aerofoil with sharp leading edge and with a jet blowing through a mid-chord slot on the upper surface in order to control the boundary layer and circulation around it. The measurements were made at low Mach number. The effect of changing the angle of blowing was studied in anticipation that this would help to control the leading edge separation bubble. It transpired that variation of the blowing angle caused little change in lift coefficient but produced an appreciable change in moment coefficient. A low pressure separation bubble was formed downstream of the slot with the jet discharging at an angle and subsequently re-attaching to the surface. This reduced the nose-up pitching moment about the quarter-chord point. The experimental results are in fair agreement with the “jet-flap” and jet entrainment theory.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 70 , Issue 666 , June 1966 , pp. 665 - 669
Copyright
Copyright © Royal Aeronautical Society 1966

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