Experimental Investigation of the Wing-Body Juncture Flow on the DLR-F6 Configuration in the ONERA S2MA Facility

Rudnik, Ralf; Sitzmann, Martin; Godard, Jean-Luc; Lebrun, Frederic

doi:10.2514/6.2009-4113

Cited by 12 publications

(4 citation statements)

References 3 publications

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“…Experimental work was also carried out relating the flow characteristics of wing-body fairing such as those presented by Rudnik et al [12]. Different measurement techniques, including pressuresensitive paint and oil-flow visualization, were used to provide more detailed flowfield information for both design and offdesign conditions.…”

Section: Related Workmentioning

confidence: 99%

Two-Level Wing-Body-Fairing Optimization of a Civil Transport Aircraft

Song¹,

Peipei²

2011

Journal of Aircraft

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A study of wing-body fairing aerodynamic optimization using a novel parameterization based on nonuniform, rational, B-spline is presented. The method allows the use of naturally bounded geometric parameters and multilevel grouping of parameters with aerodynamic significance. The issue of optimization efficiency with the use of Navier-Stokes codes necessitated by the complex nature of three-dimensional wing-body flows is solved using kriging-based surrogate modeling assisted with various data processing and visualization techniques. The last feature of the work tackles a number of constraints that are typical in the design of such fairing by incorporating the constraints directly in the parametric model. The application of the approach on the fairing design of a transport aircraft demonstrated the effectiveness of the method.

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Section: Related Workmentioning

confidence: 99%

Two-Level Wing-Body-Fairing Optimization of a Civil Transport Aircraft

Song¹,

Peipei²

2011

Journal of Aircraft

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“…An example of the interference drag is the side-of-body separation found at the wingbody junction of the DLR-F6 model [16][17][18]. Manual modification to the wing-body junction of DLR-F6 was proposed in [19] and it was later confirmed in wind tunnel experiments that the modification indeed reduces the separation and improves the lift-to-drag ratio [18,20]. Shape optimisation using the adjoint method on this configuration has been performed by Brezillon et al [21], where it was found that to effectively reduce the separation, the most critical region for shape modification is the wing-body junction rather than the wing.…”

Section: Introductionmentioning

confidence: 99%

Wing-body junction optimisation with CAD-based parametrisation including a moving intersection

Timme

Mykhaskiv

et al. 2017

Aerospace Science and Technology

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Over the past decades significant progress has been made with adjoint computational fluid dynamics solvers, which are an essential part of efficient high-fidelity aerodynamic shape optimisation. Shape parametrisation is much less mature, in particular the field is lacking efficient and automatic CAD-based parametrisation methods. The paper proposes a novel CAD-based parametrisation with CAD in the design loop such that the CAD shape can ultimately serve as a datum surface in multidisciplinary optimisation. Wing and fuselage are modelled with B-spline surfaces. The intersection line is calculated using an in-house implementation of a B-spline surface modeller and its derivative is efficiently calculated via finite differences. The proposed parametrisation method is applied to the redesign of the wingfuselage junction of the DLR-F6 model using an adjoint solver based on Reynolds-averaged Navier-Stokes equations. The moving intersection line capability enables the fuselage surface to be deformed and the resulting intersection line to move along the fixed wing during optimisation. The flow separation in the wing-body junction is substantially suppressed by an improved fuselage shape, at the cost of O(10) steady-state flow and adjoint solutions. The proposed parametrisation method represents an important step towards automated CAD-based optimisation for fully-featured aircraft characterised by complex intersecting surfaces.

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“…The aft corner separation is identified by red-colored oil, which originated on the lower surface of the wing and found its way onto the upper surface (adapted from Rudnik et al [5]). …”

Section: Time-mean Characteristicsmentioning

confidence: 99%