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Wind-tunnel tests of a heavy-class helicopter optimised for drag reduction*

Published online by Cambridge University Press:  03 June 2016

G. Gibertini ,
A. Zanotti ,
G. Droandi ,
D. Grassi ,
G. Campanardi ,
F. Auteri ,
A. Aceti  and
A. Le Pape
G. Gibertini
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
A. Zanotti*
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
G. Droandi
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
D. Grassi
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
G. Campanardi
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
F. Auteri
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
A. Aceti
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
A. Le Pape
Affiliation:
ONERA – The French Aerospace Lab, Applied Aerodynamics Department, 8 Rue des Vertugadins, F-92190, MeudonFrance
*
[email protected]
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Abstract

Wind-tunnel tests of a heavy-class helicopter model were carried out to evaluate the effectiveness of several components optimised for drag reduction by computational fluid dynamics analysis. The optimised components included different hub-cap configurations, a fairing for blade attachments and the sponsons. Moreover, the effects of vortex generators positioned on the back ramp were investigated. The optimisation effect was evaluated by comparison of the drag measurements carried out for both the original and the optimised helicopter configurations. The comprehensive experimental campaign involved the use of different measurement techniques. Indeed, pressure measurements and stereo particle image velocimetry surveys were performed to achieve a physical insight about the results of load measurements. The test activity confirms the achievement of an overall reduction of about 6% of the original model drag at cruise attitude.

Keywords

Drag reductionhelicopterwind tunnelparticle image velocimetry
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1231 , September 2016 , pp. 1446 - 1467
Copyright
Copyright © Royal Aeronautical Society 2016 

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Footnotes

*

The original version of this article was published with an incorrect list of authors. A notice detailing this has been published and the error rectified in the online and print PDF and HTML copies.

References

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