Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft

The presented work shows a preliminary analytic method for estimation of load and pressure distributions on low speed wings with flow separation and wake rollup phenomenas. A higher order vortex panel method is coupled with the numerical lifting line theory by means of iterative procedure including...

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Autor principal:	Laith W. Ismail
Formato:	article
Lenguaje:	EN
Publicado:	Al-Khwarizmi College of Engineering – University of Baghdad 2008
Materias:	??? ???? ??????? Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040
Acceso en línea:	https://doaj.org/article/8a28d42d8cdf4b1fbf58ef69310899d3
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spelling	oai:doaj.org-article:8a28d42d8cdf4b1fbf58ef69310899d32021-12-02T03:53:50ZInvestigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft1818-1171https://doaj.org/article/8a28d42d8cdf4b1fbf58ef69310899d32008-01-01T00:00:00Zhttp://www.iasj.net/iasj?func=fulltext&aId=2348https://doaj.org/toc/1818-1171The presented work shows a preliminary analytic method for estimation of load and pressure distributions on low speed wings with flow separation and wake rollup phenomenas. A higher order vortex panel method is coupled with the numerical lifting line theory by means of iterative procedure including models of separation and wake rollup. The computer programs are written in FORTRAN which are stable and efficient.<br /> The capability of the present method is investigated through a number of test cases with different types of wing sections (NACA 0012 and GA(W)-1) for different aspect ratios and angles of attack, the results include the lift and drag curves, lift and pressure distributions along the wing span taking into the consideration the effect of the angles of attack and the aspect ratios on the wake rollup. The pressure distribution on the wings shows that there is a region of constant pressure on the upper surface of the wings near the trailing edge in the middle of the wing, also there is a region of flow separation on the upper surface of the wings. A good agreement is found between the presented work results and other from previous researches. These results show that the presented method is able to capture much of flow over wings feature like separation and wake rollup. Laith W. IsmailAl-Khwarizmi College of Engineering – University of Baghdadarticle??? ???? ???????Chemical engineeringTP155-156Engineering (General). Civil engineering (General)TA1-2040ENAl-Khawarizmi Engineering Journal, Vol 4, Iss 2, Pp 59-68 (2008)
institution	DOAJ
collection	DOAJ
language	EN
topic	??? ???? ??????? Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040
spellingShingle	??? ???? ??????? Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040 Laith W. Ismail Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft
description	The presented work shows a preliminary analytic method for estimation of load and pressure distributions on low speed wings with flow separation and wake rollup phenomenas. A higher order vortex panel method is coupled with the numerical lifting line theory by means of iterative procedure including models of separation and wake rollup. The computer programs are written in FORTRAN which are stable and efficient.<br /> The capability of the present method is investigated through a number of test cases with different types of wing sections (NACA 0012 and GA(W)-1) for different aspect ratios and angles of attack, the results include the lift and drag curves, lift and pressure distributions along the wing span taking into the consideration the effect of the angles of attack and the aspect ratios on the wake rollup. The pressure distribution on the wings shows that there is a region of constant pressure on the upper surface of the wings near the trailing edge in the middle of the wing, also there is a region of flow separation on the upper surface of the wings. A good agreement is found between the presented work results and other from previous researches. These results show that the presented method is able to capture much of flow over wings feature like separation and wake rollup.
format	article
author	Laith W. Ismail
author_facet	Laith W. Ismail
author_sort	Laith W. Ismail
title	Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft
title_short	Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft
title_full	Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft
title_fullStr	Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft
title_full_unstemmed	Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft
title_sort	investigation of load and pressure distribution onwing with wake rollup for low speed aircraft
publisher	Al-Khwarizmi College of Engineering – University of Baghdad
publishDate	2008
url	https://doaj.org/article/8a28d42d8cdf4b1fbf58ef69310899d3
work_keys_str_mv	AT laithwismail investigationofloadandpressuredistributiononwingwithwakerollupforlowspeedaircraft
_version_	1718401563988328448

Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft

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