Experimental investigation of a simplified 3D high lift configuration in support of CFD validation

Johnson, P. D.; Jones, Kenneth M.; Madson, Michael D.

doi:10.2514/6.2000-4217

Cited by 61 publications

(27 citation statements)

References 7 publications

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“…In order for CFD simulations to have any scientific interest, a sound validation against test data is needed [2,16,21]. While the software has been validated on number of hydrodynamic problems, it has been decided that a specific validation on appendages shall be carried out studying three models with different geometrical characteristics exhibited in Fig.…”

Section: Cfd Validationmentioning

confidence: 99%

A hybrid numerical method to develop America’s Cup yacht appendages

Nicolopoulos¹,

Berton²,

Gouvernet³

et al. 2009

Sports Eng

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A method aimed at the development of an America's Cup racing yacht bulb is developed and validated against experimental data. The method relies heavily on Reynolds Averaged Navier Stokes computational fluid dynamics (CFD) and also factors in gravitational and aerodynamics effects through the use of a Velocity Prediction Program. Initial extensive use of towing tank results is made to be able to validate the CFD solution and thus develop a solid ground for predictive work. Then, in order to narrow down the focus on bulb developments, decoupled hypotheses are made on the influence of the hull and free surface wave. The development of a detailed performance analysis chart of a known base bulb allows the use of a relatively small series of CFD simulations together with physical hypotheses to assess any given bulb performance relative to the known base. The discussion of the results on a specific development highlights the promises and limitations of the method; final full scale results are discussed and analysed as well.

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Section: Cfd Validationmentioning

confidence: 99%

A hybrid numerical method to develop America’s Cup yacht appendages

Nicolopoulos¹,

Berton²,

Gouvernet³

et al. 2009

Sports Eng

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“…The model was developed in order to provide a database for CFD validation. This semi-span model has been tested both in the NASA Ames 12-Foot Pressurized Wind Tunnel (PWT) 30 and the NASA Langley 14-by 22-Foot Subsonic Wind Tunnel (SWT).…”

Section: High-lift Prediction Workhop Casesmentioning

confidence: 99%

FUN3D and CFL3D Computations for the First High Lift Prediction Workshop

Park

Lee-Rausch

Rumsey

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Two Reynolds-averaged Navier-Stokes codes were used to compute flow over the NASA Trapezoidal Wing at high lift conditions for the 1 st AIAA CFD High Lift Prediction Workshop, held in Chicago in June 2010. The unstructured-grid code FUN3D and the structured-grid code CFL3D were applied to several different grid systems. The effects of code, grid system, turbulence model, viscous term treatment, and brackets were studied. The SST model on this configuration predicted lower lift than the Spalart-Allmaras model at high angles of attack; the Spalart-Allmaras model agreed better with experiment. Neglecting viscous cross-derivative terms caused poorer prediction in the wing tip vortex region. Output-based grid adaptation was applied to the unstructured-grid solutions. The adapted grids better resolved wake structures and reduced flap flow separation, which was also observed in uniform grid refinement studies. Limitations of the adaptation method as well as areas for future improvement were identified.

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“…The data obtained includes tunnel inflow and out-flow conditions, tunnel free-stream turbulence levels 15 , model surface, and flow field (Particle Image Velocimetry) data. Two experiments using the same model were conducted previous to this test in the NASA Langley 14-by 22-Foot Subsonic Tunnel and in the NASA Ames 12FT Pressure Wind Tunnel 16,17 in a joint NASA/Boeing study funded under the Advanced Subsonic Transport (AST) program. While in the previous tests they examined a variety of slat and flap settings, in our test we focused on obtaining detailed flow information on one configuration, a slat setting of 30 o and a flap setting of 25 o .…”

Section: Introductionmentioning

confidence: 99%