WING OPTIMIZATION CONSTRAINED BY BOUNDARY LAYER SEPARATION USING NONLINEAR LIFTING LINE METHOD

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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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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Type

J_x - Unclassified - Peer-reviewed scientific article (Jimp, Jsc and Jost)

CEP classification

JU - Aeronautics, aerodynamics, aeroplanes

OECD FORD branch

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Project

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Continuities

R - Projekt Ramcoveho programu EK

Publication year

2009

Confidentiality

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

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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