A lifting line theory for supersonic flow applications

Jadic, I.; Constantinescu, V.

doi:10.2514/6.1991-5058

Cited by 3 publications

(1 citation statement)

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“…If sectional airfoil data is also included, this method can be extended to the entire range of angles of attack (including the stall region) and will provide C L values that are accurate to within 20% [6]. Interestingly enough, though lifting line theory was developed from incompressible, irrotational potential flow theory, it has more recently been extended to treat the subject of supersonic flows [15].…”

Section: Lifting Line Theorymentioning

confidence: 99%

Enabling Rapid Conceptual Design Using Geometry- Based Multi-Fidelity Models in VSP

Belben

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The purpose of this work is to help bridge the gap between aircraft conceptual design and analysis. Much work is needed, but distilling essential characteristics from a design and collecting them in an easily accessible format that is amenable to use by inexpensive analysis tools is a significant contribution to this goal. Toward that end, four types of reduced-fidelity or degenerate geometric representations have been defined and implemented in VSP, a parametric geometry modeler. The four types are degenerate surface, degenerate plate, degenerate stick, and degenerate point, corresponding to three-, two-, one-, and zerodimensional representations of underlying geometry, respectively.The information contained in these representations was targeted specifically at lifting line, vortex lattice, equivalent beam, and equivalent plate theories, with the idea that suitability for interface with these methods would imply suitability for use with many other analysis techniques. The ability to output this information in two plain text formatscomma separated value and Matlab script-has also been implemented in VSP, making it readily available for use.A modified Cessna 182 wing created in VSP was used to test the suitability of degenerate geometry to interface with the four target analysis techniques. All four test cases were easily completed using the information contained in the degenerate geometric types, and similar techniques utilizing different degenerate geometries produced similar results.The following work outlines the theoretical underpinnings of degenerate geometry and the fidelity-reduction process. It also describes in detail how the routines that create degenerate

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Section: Lifting Line Theorymentioning

confidence: 99%

Enabling Rapid Conceptual Design Using Geometry- Based Multi-Fidelity Models in VSP

Belben

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A numerical method for the approximation of singular integrals of functions with a pole of order two

Jadic

1994

Applied Numerical Mathematics

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Influence of weight modelling on the outcome of wing design using multidisciplinary design optimisation techniques

Mariens

Elham

Tooren

2013

Aeronaut. j. (1968)

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Weight estimation methods are categorised in different classes based on their level of fidelity. The lower class methods are based on statistical data, while higher class methods use physics based calculations. Statistical weight estimation methods are usually utilised in early design stages when the knowledge of designers about the new aircraft is limited. Higher class methods are applied in later design steps when the design is mature enough. Lower class methods are sometimes preferred in later design stages, even though the designers have enough knowledge about the design to use higher class methods. In high level multidisciplinary design optimisation (MDO) fidelity is often sacrificed to obtain models with shorter computation times. There is always a compromise required to select the proper weight estimation method for an MDO project.An investigation has been performed to study the effect of using different weight estimation methods, with low and medium levels of fidelity, on the results of a wing design using multidisciplinary design optimisation techniques. An MDO problem was formulated to design the wing planform of a typical turboprop and a turbofan passenger aircraft. The aircraft maximum take-off

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A lifting line theory for supersonic flow applications

Cited by 3 publications

References 1 publication

Enabling Rapid Conceptual Design Using Geometry- Based Multi-Fidelity Models in VSP

Enabling Rapid Conceptual Design Using Geometry- Based Multi-Fidelity Models in VSP

A numerical method for the approximation of singular integrals of functions with a pole of order two

Influence of weight modelling on the outcome of wing design using multidisciplinary design optimisation techniques

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