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Design study of Coanda devices for transonic circulation control

Published online by Cambridge University Press:  17 July 2017

M. Forster  and
R. Steijl
M. Forster*
Affiliation:
CFD Lab, School of Engineering, University of Liverpool, UK
R. Steijl
Affiliation:
Aerospace Sciences, School of Engineering, University of Glasgow, UK
*
[email protected]
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Abstract

Circulation control via blowing over Coanda surfaces at transonic freestream Mach numbers is investigated using numerical simulations. The performance and sensitivity of several circulation control devices applied to a supercritical aerofoil are assessed. Different Coanda devices were studied to assess the effect of Coanda radius-to-slot height ratio, nozzle shape and Coanda surfaces with a step. The range of operating conditions for which a supersonic Coanda jet remained attached at transonic freestream conditions were extended by increasing the radius of curvature at the slot exit for Coanda devices with a converging nozzle. Additional improvements were found by reducing the strength of shock boundary-layer interactions on the Coanda surface by expanding the jet flow using a converging-diverging nozzle and also by introducing a step between the Coanda surface and the nozzle exit. The performance when using a converging-diverging nozzle can be matched using a simple stepped Coanda device. It is shown that circulation control has the potential to match the performance of traditional control surfaces during regimes of attached flow at transonic speeds, up to an equivalent aileron deflection angle of 10°. In addition, lift augmentation ratios ΔCl/Cμ of over 100 were achieved.

Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1243 , September 2017 , pp. 1368 - 1391
Copyright
Copyright © Royal Aeronautical Society 2017 

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