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Approximate Transition Prediction for the ONERA 7AD Rotor in Forward Flight using a Structured and Unstructured URANS solver

Heister, Christoph (2016) Approximate Transition Prediction for the ONERA 7AD Rotor in Forward Flight using a Structured and Unstructured URANS solver. In: Proceedings of the AHS International 72nd Annual Forum. Mira Conference. AHS International 72nd Annual Forum, 17.-19. Mai 2016, West Palm Beach, Florida, US.

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Abstract

The simulation capabilities of the URANS solvers TAU and FLOWer of DLR have been extended in order to predict the laminar-turbulent transition onset on helicopter rotors. Therefore an approximate method for rotor blade transition prediction (RBT code) has been developed and coupled to the URANS solvers. The RBT code computes laminar boundary layer quantities based on a combined integral/Pohlhausen method. Transition is empirically predicted respecting Tollmien-Schlichting waves, laminar separation bubbles, crossflow, bypass instabilities and attachment line transition. To study the effects of blade-wake/vortex-interactions on the laminar boundary layer stability, the turbulence level of the rotor wake is taken into account for transition prediction. Test computations for two laminar flow airfoils reproduced the transition onset due to longitudinal and crossflow instabilities in close agreement to the experiment. For a helicopter rotor in forward flight, laminar-turbulent simulations were successfully demonstrated for both URANS flow solvers. A broad spectrum of different boundary layer instabilities could be identified at the blades. The predicted laminar flow at the rotor blades reduced the required rotor power by -4.5% at high speed forward flight compared to a fully turbulent simulation. The rotor thrust remained practically unaffected. The results were in good agreement between both URANS flow simulations and the experimental data.

Item URL in elib:https://elib.dlr.de/104408/
Document Type:Conference or Workshop Item (Speech)
Title:Approximate Transition Prediction for the ONERA 7AD Rotor in Forward Flight using a Structured and Unstructured URANS solver
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Heister, ChristophChristoph.Heister (at) dlr.deUNSPECIFIED
Date:17 May 2016
Journal or Publication Title:Proceedings of the AHS International 72nd Annual Forum
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Publisher:Mira Conference
Status:Published
Keywords:helicopter, rotor, transition, laminar, turbulent, URANS, boundary layer, performance, empirical, crossflow, laminar separation
Event Title:AHS International 72nd Annual Forum
Event Location:West Palm Beach, Florida, US
Event Type:international Conference
Event Dates:17.-19. Mai 2016
Organizer:AHS International
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: Braunschweig
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Helicopters
Deposited By: Heister, Christoph
Deposited On:25 May 2016 11:05
Last Modified:01 Dec 2018 19:52

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