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On the generation of a helicopter aerodynamic database

Published online by Cambridge University Press:  27 January 2016

M. Raffel ,
F. De Gregorio ,
K. de Groot ,
O. Schneider ,
W. Sheng ,
G. Gibertini  and
A. Seraudie
M. Raffel*
Affiliation:
German Aerospace Center (DLR), Goettingen, Germany
F. De Gregorio
Affiliation:
Centro Italiano Ricerche Aerospaziali (CIRA), Capua, Italy
K. de Groot
Affiliation:
German Aerospace Center (DLR), Braunschweig, Germany
O. Schneider
Affiliation:
German Aerospace Center (DLR), Braunschweig, Germany
W. Sheng
Affiliation:
Department of Aerospace Engineering, University of Glasgow, UK
G. Gibertini
Affiliation:
Dipartimento di Ingegneria Aerospaziale, Politecnico di Milano, Italy
A. Seraudie
Affiliation:
Aerodynamics and Energetics Model Department, ONERA, Toulouse, France
*
Markus.Raffel@dlr.de
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Abstract

The GOAHEAD (Generation of an Advanced Helicopter Experimental Aerodynamic Database for CFD code validation) consortium was created in the frame of an EU-project in order to create an experimental database for the validation of 3D-CFD and comprehensive aeromechanics methods for the prediction of unsteady viscous flows. This included the rotor dynamics for complete helicopter configurations, i.e. main rotor – fuselage – tail rotor configurations with emphasis on viscous phenomena like flow separation and transition from laminar to turbulent flow. The wind tunnel experiments have been performed during two weeks in the DNW-LLF on a Mach-scaled model of a modern transport helicopter consisting of the main rotor, the fuselage, control surfaces and the tail rotor. For the sake of controlled boundary conditions for later CFD validation, a closed test section has been used. The measurement comprised global forces of the main rotor and the fuselage, steady and unsteady pressures, transition positions, stream lines, position of flow separation, velocity profiles at the test section inlet, velocity fields in the model wake, vortex trajectories and elastic deformations of the main and tail rotor blades.

Type
Research Article
Information
The Aeronautical Journal , Volume 115 , Issue 1164 , February 2011 , pp. 103 - 112
Copyright
Copyright © Royal Aeronautical Society 2011

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