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Numerical and experimental validation of a morphed wing geometry using Price-Païdoussis wind-tunnel testing*

Published online by Cambridge University Press:  18 May 2016

A. Koreanschi
Affiliation:
Laboratory of Applied Research in Active Controls, Avionics and AeroServoElasticity LARCASE, École de technologie supérieure ETS, University of Quebec, Montreal, Quebec, Canada
O. Sugar-Gabor
Affiliation:
Laboratory of Applied Research in Active Controls, Avionics and AeroServoElasticity LARCASE, École de technologie supérieure ETS, University of Quebec, Montreal, Quebec, Canada
R.M. Botez*
Affiliation:
Laboratory of Applied Research in Active Controls, Avionics and AeroServoElasticity LARCASE, École de technologie supérieure ETS, University of Quebec, Montreal, Quebec, Canada

Abstract

An experimental validation of an optimised wing geometry in the Price-Païdoussis subsonic wind tunnel is presented. Two wing models were manufactured using optimised glass fibre composite and tested at three speeds and various angle-of-attack. These wing models were constructed based on the original aerofoil shape of the ATR 42 aircraft and an optimised version of the same aerofoil for a flight condition of Mach number equal to 0.1 and angle-of-attack of 0°. The aerofoil's optimisation was realised using an ‘in-house’ genetic algorithm coupled with a cubic spline reconstruction routine, and was analysed using XFoil aerodynamic solver. The optimisation was concentrated on improving the laminar flow on the upper surface of the wing, between 10% and 70% of the chord. XFoil-predicted pressure distributions were compared with experimental data obtained in the wind tunnel. The transition position was estimated from the experimental pressure data using a second derivative methodology and was compared with the transition predicted by XFoil code. The results have shown the agreement between numerical and experimental data. The wind-tunnel tests have shown that the improvement of the laminar flow of the optimised wing is higher than the value predicted numerically.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 2016 

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Footnotes

*

The authors' names were originally presented in the wrong order. A notice detailing this has been published and the error rectified in the online PDF and HTML copies.

References

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