| DOI | Resolve DOI: https://doi.org/10.2514/1.C035545 |
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| Author | Search for: Toledano, A.; Search for: Morency, F.; Search for: Weiss, J.; Search for: Broughton, C.1; Search for: Benmeddour, A.1 |
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| Affiliation | - National Research Council of Canada. Aerospace
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| Format | Text, Article |
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| Abstract | The development of flow separation on a model tested at subsonic flow conditions reaching stall is not currently accounted for by the wall-correction methodology used at the National Research Council’s (NRC’s) 5 ft trisonic wind tunnel. Consequently, although this method provides accurate wall corrections during tests in prestall conditions, it is unable to generate reliable corrections in stall. The present paper investigates the possible improvements to the singularity representation of the model, which are paramount to the “one-variable” wall-correction methodology. This revision of the model representation is based on high-fidelity free-air computational fluid dynamics solutions for the NASA Common Research Model (CRM), which are validated by experimental datasets obtained from a semispan version of the CRM tested at the NRC’s 5 ft trisonic wind tunnel. The improved potential representation is tested on solid-wall experimental wind-tunnel data to present more reliable behavior of the wall interference correction estimates when substantial wing stalling is encountered. |
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| Publication date | 2019-11 |
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| Publisher | American Institute of Aeronautics and Astronautics |
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| In | |
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| Language | English |
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| Peer reviewed | Yes |
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| Export citation | Export as RIS |
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| Report a correction | Report a correction (opens in a new tab) |
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| Record identifier | 3b2742e5-cb79-48ed-a878-5552ecde77c0 |
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| Record created | 2020-01-08 |
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| Record modified | 2020-03-16 |
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