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Erschienen in:
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2016 | OriginalPaper | Buchkapitel

Assessment of Inverse and Direct Methods for Airfoil and Wing Design

verfasst von : Mengmeng Zhang, Arthur William Rizzi

Erschienen in: Simulation-Driven Modeling and Optimization

Verlag: Springer International Publishing

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Abstract

The goal of aerodynamic design for airfoils and wings is to improve the performance of the lifting surfaces, e.g., by minimizing the drag. We consider here two approaches, the classical inverse design approach that finds the surface which produces desired pressure distributions, and the direct mathematical optimization based on local parameter searches, that is usually enabled by fast gradient computation, for example, by the adjoint method. The hybrid approach is to combine both of them. Each approach has its own pros and cons. In this chapter the approaches are assessed by application to the design of transonic RAE2822 airfoil and ONERA M6 wing.

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Vorheriges Kapitel Fast Multi-Objective Aerodynamic Optimization Using Space-Mapping-Corrected Multi-Fidelity Models and Kriging Interpolation
Nächstes Kapitel Performance Optimization of EBG-Based Common Mode Filters for Signal Integrity Applications
Fußnoten
1
This section is adapted from [5, 18].
 
4
1 drag count is defined as 104 drag coefficient; 1 lift count is defined as 103 lift coefficient.
 
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Metadaten
Titel
Assessment of Inverse and Direct Methods for Airfoil and Wing Design
verfasst von
Mengmeng Zhang
Arthur William Rizzi
Copyright-Jahr
2016
Buch
Simulation-Driven Modeling and Optimization

Print ISBN: 978-3-319-27515-4

Electronic ISBN: 978-3-319-27517-8

Copyright-Jahr: 2016

DOI
https://doi.org/10.1007/978-3-319-27517-8_4

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