CFD modelling and simulation on a lambda wing at subsonic speed

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dc.contributor.authorPrince, Simon A.
dc.contributor.authorRana, Zeeshan A.
dc.contributor.authorDi Pasquale, Davide
dc.contributor.authorPodwojewski, Claude
dc.contributor.authorZielinski, Tomas
dc.date.accessioned2025-03-21T15:08:50Z
dc.date.available2025-03-21T15:08:50Z
dc.date.freetoread2025-03-21
dc.date.issued2025-01-06
dc.date.pubOnline2025-01-03
dc.description.abstractThis paper presents and discusses the results of a study at subsonic airspeed of the aerodynamic characteristics of the Swept Wing Flow Test (SWIFT) lambda wing configuration, which was undertaken as part of the NATO AVT-298 Task Group activity on “Reynolds Number Scaling Effects on Swept Wing Flows”. While the task group studied the aerodynamics of this unconventional wing shape across the subsonic and transonic Mach number, and a wide range of Reynolds numbers via cryogenic testing in the NASA NTF wind tunnel, this paper focuses only on the Mach 0.2 conditions at a Reynolds number, based on mean chord, of 2.5 million, for which the model was tested at the ARA Transonic Wind Tunnel in the UK. Various fidelity CFD methods were employed for comparison with experimental data, over a pitch sweep from -4 to 20 degrees angle of attack, including the Viscous Full Potential (VFP) method, RANS, Unsteady RANS and Delayed Detached Eddy Simulation (DDES). The results for this case, highlight the complex 3D stall, initiating inboard, associated with this class of swept wing, which is very different from that seen on conventional swept, tapered wings typically seen on civil transport aircraft, which tends to initiate towards the tip. While the results show that, of the RANS turbulence models tested, the k-omega SST turbulence model most effectively predicted the experimental data, but none of the linear eddy viscosity models could resolve the benign stall characteristics captured in the experiment. Only the DDES method was found to effectively predict the post stall characteristics to some degree of accuracy. The VFP method generated results in a fraction of the time (seconds compared with hours), required for higher fidelity CFD solution, and was found to provide data with equivalent accuracy to RANS based methods for pre-stall conditions.
dc.description.conferencenameAIAA SCITECH 2025 Forum
dc.description.sponsorshipThe authors acknowledge the NATO AVT organization for sponsoring the activity on which this study is a small part, to the UK DSTL and the US Air Force for funding support for the experiments and ARA and NASA for their support with experimental data and computational analysis.
dc.identifier.citationPrince SA, Rana ZA, Di Pasquale D, et al., (2025) CFD modelling and simulation on a lambda wing at subsonic speed. AIAA SCITECH 2025 Forum, 6-10 January 2025 Orlando, FL. Paper number AIAA 2025-1842
dc.identifier.elementsID564678
dc.identifier.paperNoAIAA 2025-1842
dc.identifier.urihttps://doi.org/10.2514/6.2025-1842
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23654
dc.language.isoen
dc.publisherAmerican Institute of Aeronautics and Astronautics (AIAA)
dc.publisher.urihttps://arc.aiaa.org/doi/10.2514/6.2025-1842
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.titleCFD modelling and simulation on a lambda wing at subsonic speed
dc.typeConference paper
dcterms.coverageOrlando, FL
dcterms.dateAccepted2024-08-31
dcterms.temporal.endDate10-Jan-2025
dcterms.temporal.startDate6-Jan-2025

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