| DOI | Trouver le DOI : https://doi.org/10.2514/1.C035545 |
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| Auteur | Rechercher : Toledano, A.; Rechercher : Morency, F.; Rechercher : Weiss, J.; Rechercher : Broughton, C.1; Rechercher : Benmeddour, A.1 |
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| Affiliation | - Conseil national de recherches du Canada. Aérospatiale
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| Format | Texte, Article |
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| Résumé | 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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| Date de publication | 2019-11 |
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| Maison d’édition | American Institute of Aeronautics and Astronautics |
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| Dans | |
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| Langue | anglais |
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| Publications évaluées par des pairs | Oui |
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| Exporter la notice | Exporter en format RIS |
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| Signaler une correction | Signaler une correction (s'ouvre dans un nouvel onglet) |
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| Identificateur de l’enregistrement | 3b2742e5-cb79-48ed-a878-5552ecde77c0 |
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| Enregistrement créé | 2020-01-08 |
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| Enregistrement modifié | 2020-03-16 |
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