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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, 2016-05-17 - 2016-05-19, West Palm Beach, Florida, US.

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Kurzfassung

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.

elib-URL des Eintrags:https://elib.dlr.de/104408/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Approximate Transition Prediction for the ONERA 7AD Rotor in Forward Flight using a Structured and Unstructured URANS solver
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Heister, ChristophChristoph.Heister (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:17 Mai 2016
Erschienen in:Proceedings of the AHS International 72nd Annual Forum
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Verlag:Mira Conference
Status:veröffentlicht
Stichwörter:helicopter, rotor, transition, laminar, turbulent, URANS, boundary layer, performance, empirical, crossflow, laminar separation
Veranstaltungstitel:AHS International 72nd Annual Forum
Veranstaltungsort:West Palm Beach, Florida, US
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:17 Mai 2016
Veranstaltungsende:19 Mai 2016
Veranstalter :AHS International
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Luftfahrt
HGF - Programmthema:Hubschrauber
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L RR - Rotorcraft Research
DLR - Teilgebiet (Projekt, Vorhaben):L - Der virtuelle Drehflügler (alt)
Standort: Braunschweig
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Hubschrauber
Hinterlegt von: Heister, Christoph
Hinterlegt am:25 Mai 2016 11:05
Letzte Änderung:24 Apr 2024 20:09

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