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Dynamic Stall on a Pitching Double-Swept Rotor Blade Tip

Lütke, Benjamin (2017) Dynamic Stall on a Pitching Double-Swept Rotor Blade Tip. Dissertation, Technische Universität München.

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Official URL: http://nbn-resolving.de/urn/resolver.pl?urn:nbn:de:bvb:91-diss-20170908-1359091-1-8

Abstract

Dynamic stall is experimentally and numerically investigated on a pitching double-swept helicopter rotor blade tip. The aerodynamic and structural design of the instrumented wind tunnel model is presented. The influence of many aerodynamic parameters on the dynamic stall is shown. The crossflow velocities lead to a delayed stall and a decreased lift at the kink. Time shifted flow separation occurs inboard and outboard of the kink. A sharp gradient in the global pitching moment is avoided.

Item URL in elib:https://elib.dlr.de/117699/
Document Type:Thesis (Dissertation)
Title:Dynamic Stall on a Pitching Double-Swept Rotor Blade Tip
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Lütke, Benjaminbenjamin.luetke (at) dlr.deUNSPECIFIED
Date:8 September 2017
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Number of Pages:106
Status:Published
Keywords:dynamic stall, helicopter, double-swept blade tip, wind tunnel, carbon fiber reinforced plastic model, CFRP, structural design, separated flow, Dynamischer Strömungsabriss, Hubschrauber, doppelt-gepfeilte Rotorblattspitze, Windkanal, Faserverbundbauweise, strukturelle Auslegung, abgelöste Strömung
Institution:Technische Universität München
Department:Fakultät für Maschinenwesen
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 Virtual Aerodynamic Rotorcraft
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Aeroelastic Experiments
Deposited By: Mai, Holger
Deposited On:22 Dec 2017 08:39
Last Modified:31 Jul 2019 20:15

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