Unsteady Wake of the NASA Common Research Model in Low-Speed Stall

Waldmann, Andreas; Gansel, Philipp P.; Lutz, Thorsten; Krämer, Ewald

doi:10.2514/1.c033413

Cited by 18 publications

(13 citation statements)

References 15 publications

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“…After comparing the calculated and experimental results, the authors concluded that the DDES calculation results were more reliable and could reveal more detailed flow information and vortex structures than those of RANS. What is more, Waldmann et al [16], Lutz et al [17], and Zimmermann et al [18] numerically investigated the influence of unsteady wake on the tail of NASA CRM wing-body-tail configuration under poststall condition by the DDES method based on a TAU solver. Escobar et al [19] made use of the DES97 method in ANSYS Fluent to make a detailed analysis of the flow around the DLR-F11 high-lift configuration.…”

Section: Introductionmentioning

confidence: 99%

Investigation and Improvement of Stall Characteristic of High-Lift Configuration without Slats

Yang

Jin

et al. 2019

International Journal of Aerospace Engineering

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In order to simplify the manufacturing process or because of the limitation of the propulsion system, business jet, small civil airplane, and turboprop aircraft are always designed without leading-edge slats, which poses a great challenge to the flight safety during takeoff and landing. Focusing on the low-speed stall and poststall conditions, we investigated the aerodynamic characteristics and flow mechanism of high-lift configuration without slats using an improved delayed detached eddy simulation (IDDES) model which is validated by numerical simulations of the Common Research Model (CRM). Based on the analysis of the calculated results, conclusion can be made that the stall behavior of the configurations is directly related to the onset and evaluation of flow separation on the suction side. And through further research, an efficient evaluation method that is capable of qualitatively predicting the stall performance of two-element high-lift configuration by stall angle distribution of wing sections is proposed. By using the evaluation method, together with design rules summarized from the present study, high-lift configuration with mild-stall characteristic can be obtained in the preliminary stage of design.

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Section: Introductionmentioning

confidence: 99%

Investigation and Improvement of Stall Characteristic of High-Lift Configuration without Slats

Yang

Jin

et al. 2019

International Journal of Aerospace Engineering

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“…The test data has allowed the characterization of the unsteady development of massively separated wing flows, and how the wake development progresses towards the empennage. The test data have also been compared with complex numerical simulations, considering aeroelastic wing deformationn [16][17][18].…”

Section: Project For the Etw Wind Tunnel: Time-resolved Wake Measuremmentioning

confidence: 99%

ESWIRP: European Strategic Wind tunnels Improved Research Potential program overview

Boyet

2018

CEAS Aeronaut J

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aiming at improving the performance capabilities of three strategic wind tunnels in Europe, by strengthening the cooperation between these wind tunnels in a new consortium. The research consortium members are Office National d'Etudes et de Recherches Aérospatiales (operating the S1MA as its largest sonic wind tunnel), German-Dutch wind tunnels [operating the large low-speed facility (LLF) as its largest low-speed wind tunnel], and European transonic wind tunnel (ETW) (operating its cryogenic wind tunnel). Together, these wind tunnels cover a wide range of experimental capabilities of relevance to civil aviation and aeronautical research in general. The project started in October 2009 for a period of 5 years. The European financial contribution was €7.2 million. The project consist of two major parts: (1) improvements to the testing infrastructure; and (2) the provision of wind tunnel access to research groups which do not usually have the means to access such large-scale test facilities. These topics also involved public dissemination and information activities. Although the tunnels covered in this project are of a complementary nature, the infrastructure activities were joined together, by a common representation of, and approach to, the tunnel performance characteristics. To this end, a generic model of a virtual wind tunnel was developed, enabling operators to assess the effect of the control parameters upon the testing conditions. The final aim of all participants was to provide the user community with an improved set of capabilities to test their innovative ideas. To provide better access to these three major wind tunnels, mainly research groups from European universities were contacted. The approach taken has included maximum transparency of the process and support of the researchers by the organizations responsible for the tunnels. In addition, when possible, we encouraged research groups to work together, to obtain the full benefit of economies of scale in research projects. ESWIRP responded to the targeted approach of the Integrating Activities of the FP7 Capacities Work Program: Networking activities, essentially focused around four topics: (1) organization of information campaigns, lectures and workshops to disseminate knowledge between the partners and future users. (2) Opening of a website for the consultation of wind tunnel standards. (3) Exchange of personnel between the Consortium partners, to foster the spread of good practices and the exchange of technical know-how. (4) Joint development of a reference wind tunnel parameter database. Trans-national access and/or testing services: after the call for proposals by the facility providers, groups of researchers had the opportunity to benefit from free wind tunnel services, including technical assistance to support the corresponding scientific research team(s). Joint research activities, innovative modeling of wind tunnels has helped designers to make better decisions, before the implementation of any novel hardware. Based on a generic finite volume t...

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“…The 4th 19 and 5th AIAA Drag Prediction Workshops 20 employed it. Various other publications using the CRM have appeared in the past several years, including fluid-structure simulation (Keye et al 21 ), combined wind tunnel and CFD studies (Rivers et al, 8 Lutz et al, 10 Waldmann et al 11 ) and many more. The wind tunnel model used in the ETW is a 2.7% scale model of the CRM with a wingspan of 1.586 m. The model's horizontal tailplane was set to the neutral position (0 • ) and no nacelles were mounted on the wings.…”

Section: Iib Wind Tunnel Modelmentioning

confidence: 99%

“…The grid is part of a grid family thas has been extensively used in various works at IAG. 11,12 Its baseline version has been described by Gansel et al 22 It is a hybrid grid consisting of tetrahedra, with boundary layers resolved by prism and hexahedron layers. The boundary layer grids are adapted to the local flow conditions, so as to achieve a smooth distribution of y + over the surface in the presence of a boundary layer that grows with downstream distance.…”

Section: Iiia Gridmentioning

confidence: 99%

“…Such a situation occurred during the European Strategic Wind Tunnel Improved Research Potential (ESWI RP ) measurement campaign, a research activity funded by the European Commission's 7th framework program. The authors of this work encountered the issue during the preparation for unsteady computations at high angles of attack, [10][11][12] revealing differences in force and pitching moment coefficients between experiments and CFD. This motivated the present study, with the goal being the understanding and quantification of the differences between simulation and measurement results.…”

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confidence: 99%

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Wind Tunnel Support System Influence on NASA Common Research Model at Low Speed Conditions

Waldmann

Lutz

Kraemer

2016

32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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Computational studies were conducted in order to gain an understanding and to quantify the impact of the model support system and aeroelastic wing deformation on the Common Research Model at subsonic inflow conditions at Re∞ = 11.6 • 10 6. Comparisons between results obtained in the European Transonic Windtunnel and from simulations using TAU reveal the extent of the modeling error introduced by neglecting the support structure. RANS simulations with and without the support system show that it has a near-field effect on the model's rear fuselage, significantly altering the pressure field and thereby impacting the force coefficients, most significantly drag and pitching moment. Aeroelastic wing deformation was also included in the investigation, showing non-negligible impact on the forces. The inclusion of the support system and wing deformation, as well as the use of advanced turbulence models, were shown to promise considerable error reduction potential in comparative studies between wind tunnel and simulation data.

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Unsteady Wake of the NASA Common Research Model in Low-Speed Stall

Cited by 18 publications

References 15 publications

Investigation and Improvement of Stall Characteristic of High-Lift Configuration without Slats

Investigation and Improvement of Stall Characteristic of High-Lift Configuration without Slats

ESWIRP: European Strategic Wind tunnels Improved Research Potential program overview

Wind Tunnel Support System Influence on NASA Common Research Model at Low Speed Conditions

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