Communication Dans Un Congrès Année : 2024

Testing the Full-Span High-Lift Common Research Model at the ONERA F1 Pressurized Low-Speed Wind Tunnel

Essai de la High-Lift Common Research Model dans la soufflerie basse vitesse pressurisée ONERA F1

Résumé

This paper presents the main features and outcomes of the wind tunnel testing of the High-Lift Common Research Model full-span model in the ONERA F1 pressurized low-speed wind tunnel. Two complementary test campaigns were carried out in 2022 and 2023, and included variation in model configurations, angle of attack, angle of sideslip, Mach and Reynolds numbers, and included force and moment, pressure, wing deformation, and flow visualization data. The main elements of the test methodology are reviewed to better appreciate the quality of the database, in terms of uncertainty, repeatability, and wall and support corrections. A selection of results is presented regarding longitudinal and lateral characteristics, the build-up of the landing configuration, Mach and Reynolds number effects, and flap setting effect. A special focus is accorded to data used in the fifth High-Lift Prediction Workshop.

As a consequence, the determination of aircraft high-lift performance strongly relies on wind tunnel testing, which also comes with some limitations, such as compromises in the geometrical modeling of the aircraft, or Reynolds number effects.

In order to advance both CFD and wind tunnel capabilities, a High-Lift Common Research Model (CRM-HL) ecosystem has been started to promote dialogue between computational and experimental researchers and practitioners [4]. This ecosystem benefited from a first high-lift configuration [5] based on the high-speed Common Research Model (CRM) shape [6][7]. This configuration was used to manufacture a 10% semi-span model that was first tested at the NASA Langley Research Center 14-by-22 foot atmospheric wind tunnel in late 2018 [8][9], then at the Qinetiq 5 m pressurized wind tunnel in 2019 [10], and again in the 14-by-22 foot tunnel in 2020/2021 for acoustics purpose [11]. Geometry and results from the test in the Qinetiq 5 m tunnel were used in the fourth HLPW (HLPW-4) [12], which also stimulated considerable computational efforts, e.g. [13]. This geometry was however limited by the mechanical capabilities of the 10% semi-span model, so that between 2020 and 2021, some further small improvements were brought to the configuration, to come up with the present "Initial reference configuration" [14], that is used in the fifth HLPW (HLPW-5). Based on this shape, a 1/19.5 (≈5.9%) full-span model was designed and manufactured at ONERA, and it was called LRM-HL for "Large Reference Model -High-Lift". This model and test is a follow-up of a broader effort from ONERA to participate in the CRM community, which already produced wind tunnel tests and flow simulations on the high-speed configuration [15][16][17][18]. This effort aims at the following objectives:

• to build an open experimental capability and database for the scientific community,

• to use the models as test benches for the development and demonstration of testing techniques,

• to enable comparisons across wind-tunnels,

• to be a long-term reference model for the wind-tunnels. In many aspects, these goals were aligned with those exposed in [19] for the purpose of CFD validation, so that recommendations and requirements from [19] could be taken into account.

The present paper introduces the F1 wind tunnel (section II), the LRM-HL model (section III) and the experimental methodologies (section IV). It then presents some results of the test campaigns respectively carried out between March 29 th and April 19 th , 2022 and between February 2 nd and February 15 th , 2023 (section V). Most of the results presented are related to the test cases 2 and 3 selected in the HPLW-5. In that respect, this paper can be regarded as introducing the experimental dataset used as validation data in the workshop. Data sharing policy and availability are presented in section VI. This paper extends a previous AIAA publication [20], as it now presents and compares results from two test campaigns, and it reveals results that were previously presented unscaled. In order to avoid constantly referring the reader to this previous publication, some parts of it are repeated in the present paper.

Cet article présente les principales caractéristiques et résultats des essais en soufflerie de la maquette complète High-Lift Common Research Model dans la soufflerie à basse vitesse pressurisée ONERA F1. Deux campagnes d'essais complémentaires ont été réalisées en 2022 et 2023, incluant des variations dans les configurations de la maquette, de l'angle d'attaque, l'angle de dérapage, des nombres de Mach et de Reynolds, et comprenant des données de force et de moment, de pression, de déformation de l'aile, et de visualisation de l'écoulement. Les principaux éléments de la méthodologie des essais sont examinés afin de mieux apprécier la qualité de la base de données, en termes d'incertitude, de répétabilité, et de corrections de parois et de support. Une sélection de résultats est présentée concernant les caractéristiques longitudinales et latérales, la configuration d'atterrissage, les effets des nombres de Mach et de Reynolds, et l'effet des réglages des volets. Un accent particulier est mis sur les données utilisées dans le cinquième High-Lift Prediction Workshop.
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Recherche Data Gouv

Cite 10.57745/B8VDHO Jeu de données Mouton, Sylvain, 2024, "Experiment with the Full Span High Lift Common Research Model at the ONERA F1 Pressurized Low Speed Wind Tunnel", https://doi.org/10.57745/B8VDHO, Recherche Data Gouv, V1

Dates et versions

hal-04690266 , version 1 (06-09-2024)

Identifiants

Citer

Sylvain Mouton, Grégoire Charpentier, Annabelle Lorenski. Testing the Full-Span High-Lift Common Research Model at the ONERA F1 Pressurized Low-Speed Wind Tunnel. AIAA Aviation 2024, Jul 2024, Las Vegas (NV), United States. pp.AIAA 2024-3512, ⟨10.2514/6.2024-3512⟩. ⟨hal-04690266⟩

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