elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Contact | Deutsch
Fontsize: [-] Text [+]

A comprehensive PIV measurement campaign on a fully equipped helicopter model

de Gegorio, Fabrizio and Pengel, Kurt and Kindler, Kolja (2012) A comprehensive PIV measurement campaign on a fully equipped helicopter model. Experiments in Fluids, Vol. 53 (1), pp. 37-49. Springer Verlag, Berlin. DOI: 10.1007/s00348-011-1185-0. ISSN 0723-4864 .

Full text not available from this repository.

Official URL: http://www.springer.com

Abstract

The flow field around a helicopter is characterised by its inherent complexity including effects of fluid– structure interference, shock–boundary layer interaction, and dynamic stall. Since the advancement of computational fluid dynamics and computing capabilities has led to an increasing demand for experimental validation data, a comprehensive wind tunnel test campaign of a fully equipped and motorised generic medium transport helicopter was conducted in the framework of the GOAHEAD project. Different model configurations (with or without main/tail rotor blades) and several flight conditions were investigated. In this paper, the results of the three-component velocity field measurements around the model are surveyed. The effect of the interaction between the main rotor wake and the fuselage for cruise/tail shake flight conditions was analysed based on the flow characteristics downstream from the rotor hub and the rear fuselage hatch. The results indicated a sensible increment of the intensity of the vortex shedding from the lower part of the fuselage and a strong interaction between the blade vortex filaments and the wakes shed by the rotor hub and by the engine exhaust areas. The pitch-up phenomenon was addressed, detecting the blade tip vortices impacting on the horizontal tail plane. For high-speed forward flight, the shock wave formation on the advancing blade was detected, measuring the location on the blade chord and the intensity. Furthermore, dynamic stall on the retreating main rotor blade in high-speed forward flight was observed at r/R = 0.5 and 0.6. The analysis of the substructures forming the dynamic stall vortex revealed an unexpected spatial concentration suggesting a rotational stabilisation of large-scale structures on the blade.

Document Type:Article
Additional Information:ISSN: 1432-1114 (Online), Published online: 14. Sept. 2011
Title:A comprehensive PIV measurement campaign on a fully equipped helicopter model
Authors:
AuthorsInstitution or Email of Authors
de Gegorio, FabrizioCentro Italiano Ricerche Aerospaziali (CIRA), Via Maiorise, 81043 Capua (CE), Italy
Pengel, KurtDNW
Kindler, KoljaMax-Planck-Institute for Marine Microbiology, HB
Date:2012
Journal or Publication Title:Experiments in Fluids
Refereed publication:Yes
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:Vol. 53
DOI:10.1007/s00348-011-1185-0
Page Range:pp. 37-49
Publisher:Springer Verlag, Berlin
ISSN: 0723-4864
Status:Published
Keywords:shock–boundary layer, helicopter, rotor blades, velocity field measurements, large-scale structures
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Rotorcraft
DLR - Research area:Aeronautics
DLR - Program:L RR - Rotorcraft Research
DLR - Research theme (Project):L - The Innovative Rotorcraft
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Helicopters
Deposited By: Ilka Micknaus
Deposited On:18 Oct 2011 15:11
Last Modified:26 Mar 2013 13:31

Repository Staff Only: item control page

Browse
Search
Help & Contact
Informationen
electronic library is running on EPrints 3.3.12
Copyright © 2008-2012 German Aerospace Center (DLR). All rights reserved.