WING OPTIMIZATION CONSTRAINED BY BOUNDARY LAYER SEPARATION USING NONLINEAR LIFTING LINE METHOD
The result's identifiers
Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F09%3A%230000922" target="_blank" >RIV/00010669:_____/09:#0000922 - isvavai.cz</a>
Result on the web
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DOI - Digital Object Identifier
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Alternative languages
Result language
angličtina
Original language name
WING OPTIMIZATION CONSTRAINED BY BOUNDARY LAYER SEPARATION USING NONLINEAR LIFTING LINE METHOD
Original language description
A nonlinear generalization of the classical lifting line method for slender wings is described, along with a free software implementation. The new method allows employing nonlinear airfoil section lift data including stall region of angles of attack, either computed by a 2D method or experimental ones. Thus the method gives more realistic results at higher angles of attack. Amongst other quantities, the method is able to estimate the span-wise position where the separation of the boundary layer starts to develop, while still being orders of magnitude faster than a CFD analysis.
Czech name
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Czech description
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Classification
Type
J<sub>x</sub> - Unclassified - Peer-reviewed scientific article (Jimp, Jsc and Jost)
CEP classification
JU - Aeronautics, aerodynamics, aeroplanes
OECD FORD branch
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Result continuities
Project
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Continuities
R - Projekt Ramcoveho programu EK
Others
Publication year
2009
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů
Data specific for result type
Name of the periodical
Czech Aerospace Proceedings / Letecký zpravodaj
ISSN
1211-877X
e-ISSN
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Volume of the periodical
3/2009
Issue of the periodical within the volume
3
Country of publishing house
CZ - CZECH REPUBLIC
Number of pages
5
Pages from-to
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UT code for WoS article
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EID of the result in the Scopus database
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