From geometry to CFD grids—An automated approach for conceptual design

Transonic airfoil and wing design using inverse and direct methods. A hybrid inverse/direct-optimization method for subsonic/transonic airfoil and wing shape design is presented with application to a range of airfoil and wing cases, in preparation for the test cases defined for the Special Session of SciTech 2015. The method is hybrid in the sense that it combines the traditional inverse design technique with a gradient-based procedure to approach the optimum aerodynamic surface. This paper emphasizes the first part, the development of SCID, the Surface Curvature Inverse Design method, the theory upon which it is based, including many of the details involved with shocks, smoothing and cross flow. The application of SCID to wing design poses many challenges, and how they are met is discussed in the context of a number of inverse design test cases for airfoils and wings. But it also includes results from the adjoint optimization and compares them. The procedure works well for airfoils and the twist optimization for wings. The real benchmarks for our hybrid approach are the three Optimization Discussion Group design problems. Solutions are presented for the drag minimization of the airfoil test cases along with the wing twist optimization problem, and conclusions are drawn from the results obtained. A swept-back transonic wing is designed by SCID with encouraging results, showing that SCID works fine with wings. Work has started on the drag minimization of the CRM wing in transonic flight, and final results will be presented in a future paper.

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“…[4][5][6][7][8][9][10], from which the new airfoil shape can be integrated by i solving the second-order boundary value problem(2), or…”

Section: Solutions To Scementioning

confidence: 99%

Transonic Airfoils and Wings Design Using Inverse and Direct Methods

Zhang

Rizzi

Nangia

2015

53rd AIAA Aerospace Sciences Meeting

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“…Most are custom built (e.g., [26]) with some based on existing tools (e.g., Modelcenter in [23]) and some fully open source (e.g., [27]). Well known tools in this category include VSP [28] and CEASIOM/CPACS [29,30]. A very good and extensive overview of these topics and the wider domain of systems engineering is given by Price, Raghunathan and Curran in [8].…”

Section: B Research Contextmentioning

confidence: 99%

Value-Based Decision Environment: Vision and Application

Gorissen

Quaranta

Ferraro

et al. 2014

Journal of Aircraft

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The ever increasing complexity and environmental constraints associated with aerospace and defense projects are putting pressure on traditional organizational structures for design decision making. No longer can the design problem be assimilated and steered by a single chief engineer. Rather, in order to nd consensus, design involves a complex iterative process between the dierent specialist committees (weights, aerodynamics, structures, cost, etc.). Furthermore, there is a growing need to take into account the life cycle implications of low level design decisions in addition to their more direct implications on performance. The Decision Environment for Complex Designs (DECODE) project at the University of Southampton aims to explore how the design process may be streamlined under these circumstances. The case study presented here centers around a maritime surveillance UAV for search and rescue tasks, developed in association with the UK Coastguard. The focus is on value driven design and how advances in software engineering, rationale capture, operational simulation, and rapid prototyping can be leveraged to create an integrated design suite that allows the rapid design and manufacture of low cost civilian UAVs.

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“…• Geometry module CPACScreator-sumo 17,26 A customized geometry construction system coupled to automated surface and volume grid generators; Resulting model exported to CAD via IGES standard.…”

Section: 10-15mentioning

confidence: 99%

Collaborative Aircraft Design Methodology using ADAS Linked to CEASIOM

Zhang

Rizzi

Nicolosi

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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The aircraft design stages, conceptual and preliminary, are necessarily collaborative by their very nature. An example design carried out in this paper brings the collaborative aspects of design to life by two academic groups, one in Naples and one in Stockholm, using their own tools ADAS and CEASIOM, working respectively on conceptual and preliminary design. The ADAS tool is primarily empirically-based design methodology, and the CEA-SIOM tool is primarily physics-based design methodology. The example chosen is a FAR-23 compliant 16-seat twin turboprop aircraft. The high-wing configuration resulting from the ADAS conceptual design is the down-selected to CEASIOM where a water-tight model of the geometry is constructed, a volume grid is generated and 16 flight conditions are simulated by solutions of the Euler equations, some with propeller off, and others with propeller in order to judge the effect of the propeller wash over the main wing and horizontal tail surface. Detailed comparisons between ADAS results and CEASIOM results for stability & control characteristics are carried out. In general there is reasonable agreement between the two sets, considering that the empiricisms in ADAS account for viscous effects where as the CEASIOM are purely inviscid (but nonlinear). The largest discrepancy appears in the pitching moment contribution from the horizontal tail, and various explanations for this are suggested, including possible effects of the main wing downwash and wake on the tail.

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From geometry to CFD grids—An automated approach for conceptual design

Cited by 37 publications

References 5 publications

Transonic Airfoils and Wings Design Using Inverse and Direct Methods

Transonic Airfoils and Wings Design Using Inverse and Direct Methods

Value-Based Decision Environment: Vision and Application

Collaborative Aircraft Design Methodology using ADAS Linked to CEASIOM

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