Study of the subsonic wall interference in stall of the NASA CRM at the NRC 1.5 m Trisonic Wind Tunnel

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DOIResolve DOI: http://doi.org/10.2514/6.2017-4130
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TypeArticle
Proceedings title33rd AIAA Aerodynamic Measurement Technology and Ground Testing Conference
Conference33rd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, 5-9 June 2017, Denver, Colorado, USA
ISSN978-1-62410-502-9
Pages# of pages: 12
AbstractThe development of flow separation on a model tested at subsonic flow conditions reaching stall is not currently accounted for by the one-variable method, which is the wall correction methodology used at the NRC 1.5 m Trisonic Wind Tunnel. Consequently, while this method provides accurate wall corrections during real-time tests in pre-stall conditions, it is unable to generate reliable corrections in stall conditions. In order to improve the potential theory representation of the model that is essential to the one-variable method, experimental results from a recent test campaign on a semispan version of the NASA Common Research Model (CRM) are used in combination with free-air RANS numerical simulations. The computational results are used to characterize the separation bubble that develops on the model so that it can be represented by an array of singularities added to the current potential theory model of the wing. Additionally, in a modified version of the one-variable method, the potential theory representation of the model is replaced by free-air CFD results to investigate the behavior of wall corrections for a contemporary wide-body transport aircraft tested at low-speed subsonic flow reaching stall conditions.
Publication date
PublisherAmerican Institute of Aeronautics and Astronautics
LanguageEnglish
AffiliationNational Research Council Canada; NRC Institute for Aerospace Research; Aerospace
Peer reviewedYes
NPARC number23002253
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Record identifier795e4a23-099a-4008-9ac4-3c4b64788635
Record created2017-09-14
Record modified2017-09-14
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