elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Impressum | Kontakt | English
Schriftgröße: [-] Text [+]

A comprehensive PIV measurement campaign on a fully equipped helicopter model

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

Dieses Archiv kann nicht den gesamten Text zur Verfügung stellen.

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

Kurzfassung

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.

Dokumentart:Zeitschriftenbeitrag
Zusätzliche Informationen:ISSN: 1432-1114 (Online), Published online: 14. Sept. 2011
Titel:A comprehensive PIV measurement campaign on a fully equipped helicopter model
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
de Gegorio, FabrizioCentro Italiano Ricerche Aerospaziali (CIRA), Via Maiorise, 81043 Capua (CE), Italy
Pengel, KurtDNW
Kindler, KoljaMax-Planck-Institute for Marine Microbiology, HB
Datum:2012
Erschienen in:Experiments in Fluids
Referierte Publikation:Ja
In SCOPUS:Ja
In ISI Web of Science:Ja
Band:Vol. 53
DOI :10.1007/s00348-011-1185-0
Seitenbereich:Seiten 37-49
Verlag:Springer Verlag, Berlin
ISSN: 0723-4864
Status:veröffentlicht
Stichwörter:shock–boundary layer, helicopter, rotor blades, velocity field measurements, large-scale structures
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Luftfahrt
HGF - Programmthema:Drehflügler
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L RR - Drehflüglerforschung
DLR - Teilgebiet (Projekt, Vorhaben):L - Der innovative Drehflügler
Standort: Göttingen
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Hubschrauber
Hinterlegt von: Ilka Micknaus
Hinterlegt am:18 Okt 2011 15:11
Letzte Änderung:26 Mär 2013 13:31

Nur für Mitarbeiter des Archivs: Kontrollseite des Eintrags

Blättern
Suchen
Hilfe & Kontakt
Informationen
electronic library verwendet EPrints 3.3.12
Copyright © 2008-2013 Deutsches Zentrum für Luft- und Raumfahrt (DLR). Alle Rechte vorbehalten.