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Validation study for prediction of iced aerofoil aerodynamics

Published online by Cambridge University Press:  03 February 2016

S. Marques ,
K. J. Badcock ,
J. H. M. Gooden ,
S. Gates  and
W. Maybury
S. Marques
Affiliation:
[email protected], Department of Engineering, University of Liverpool, Liverpool, UK
K. J. Badcock
Affiliation:
[email protected]
J. H. M. Gooden
Affiliation:
National Aerospace Laboratory NLR, Amsterdam, The Netherlands
S. Gates
Affiliation:
AgustaWestland Yeovil, UK
W. Maybury
Affiliation:
AgustaWestland Yeovil, UK
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Abstract

Ice accretions can significantly change the aerodynamic performance of wings and rotor blades. Significant performance degradation can occur when ice accreations cause regions of separated flow, to predict this change implies, at a minimum, the solution of the Reynolds-Averaged Navier-Stokes equations. This paper presents validation for two generic cases involving the flow over aerofoil sections with added synthetic ice shapes. Results were obtained for two aerofoils, namely the NACA 23012 and a generic multi-element configuration. These results are compared with force and pressure coefficient measurements obtained in the NASA LTPT wind-tunnel for the NACA 23012, and force, PIV and boundary-layer measurements obtained at DNW for the multi-element case. The level of agreement is assessed in the context of industrial requirements.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1152 , February 2010 , pp. 103 - 111
Copyright
Copyright © Royal Aeronautical Society 2010 

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