Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah

The surfaces that support an aircraft by means of dynamic reaction on the air are called wings. Regardless of the type of lifting surface, its aerodynamic characteristics of the wing section will strongly affected by the shape of the wing section (called airfoil). The wing characteristics may be pre...

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Main Author:	Abdullah, Abdul Rahman
Format:	Student Project
Language:	English
Published:	Faculty of Mechanical Engineering 1999
Subjects:	Production management. Operations management
Online Access:	http://ir.uitm.edu.my/id/eprint/25908/ http://ir.uitm.edu.my/id/eprint/25908/1/PPd_ABDUL%20RAHMAN%20ABDULLAH%20EM%2000_5.pdf

id	uitm-25908
recordtype	eprints
spelling	uitm-259082019-10-01T08:03:50Z http://ir.uitm.edu.my/id/eprint/25908/ Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah Abdullah, Abdul Rahman Production management. Operations management The surfaces that support an aircraft by means of dynamic reaction on the air are called wings. Regardless of the type of lifting surface, its aerodynamic characteristics of the wing section will strongly affected by the shape of the wing section (called airfoil). The wing characteristics may be predicted from the known aerodynamic characteristics of the wing section. A considerable body of aerodynamic theory has been developed whereby it is possible to calculate some of the important characteristics of wing sections, one being the use of PANEL METHOD and with the aide of computers. By the beginning of the 20th century, methods of hydrodynamics had been successfully applied to airfoils so as to allow the prediction of lifting characteristics for airfoil shapes, mathematically. These special shapes did not represent the optimum in airfoil performance, and experimental methods (that is the wind tunnel testing) guided by theory were used to determine the characteristics of arbitrary shaped airfoils. Eventually, the numerical technique of panel method has come into widespread use since 1970s. Panel Method computer codes, is used for the purpose of estimating aerodynamic characteristics of two-dimensional airfoil sections in ideal flows of negligible compressibility and viscosity effects, with a primary intention as a preliminary evaluation tool used to obtain quick estimations of configuration aerodynamics. It is not the intent to replace wind tunnel or more rigorous analytical results, but rather to provide an efficient means of estimating vehicle aerodynamic characteristics and preliminary design stages. Thus, base on these preliminary design estimation, this project will assimillate the Utilization of Panel Method Using Fortran (a reliable and convenience way to represent linear equations and other listings through computer programs) to predict the aerodynamic sectional airfoil coefficients namely Cl (lift), Cd (drag) and Cm (moment) so as further analysis of aerodynamic characteristics can be done with the results obtained. NACA 0009 Symmetrical Airfoil and NACA 23018 Cambered Airfoil configuration is used as a comparable results with the one obtained from Abbot and Von Doenhoff Airfoil Data. Hopefully with this effort, those whose interest is Computational Aerodynamics, particularly with the use of Panel Method, will gain tremendously. To appreciate the PROGRAM PANEL is to really understand the gist of Panel Method. Enjoy reading. Faculty of Mechanical Engineering 1999 Student Project NonPeerReviewed text en http://ir.uitm.edu.my/id/eprint/25908/1/PPd_ABDUL%20RAHMAN%20ABDULLAH%20EM%2000_5.pdf Abdullah, Abdul Rahman (1999) Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah. [Student Project] (Unpublished)
repository_type	Digital Repository
institution_category	Local University
institution	Universiti Teknologi MARA
building	UiTM Institutional Repository
collection	Online Access
language	English
topic	Production management. Operations management
spellingShingle	Production management. Operations management Abdullah, Abdul Rahman Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah
description	The surfaces that support an aircraft by means of dynamic reaction on the air are called wings. Regardless of the type of lifting surface, its aerodynamic characteristics of the wing section will strongly affected by the shape of the wing section (called airfoil). The wing characteristics may be predicted from the known aerodynamic characteristics of the wing section. A considerable body of aerodynamic theory has been developed whereby it is possible to calculate some of the important characteristics of wing sections, one being the use of PANEL METHOD and with the aide of computers. By the beginning of the 20th century, methods of hydrodynamics had been successfully applied to airfoils so as to allow the prediction of lifting characteristics for airfoil shapes, mathematically. These special shapes did not represent the optimum in airfoil performance, and experimental methods (that is the wind tunnel testing) guided by theory were used to determine the characteristics of arbitrary shaped airfoils. Eventually, the numerical technique of panel method has come into widespread use since 1970s. Panel Method computer codes, is used for the purpose of estimating aerodynamic characteristics of two-dimensional airfoil sections in ideal flows of negligible compressibility and viscosity effects, with a primary intention as a preliminary evaluation tool used to obtain quick estimations of configuration aerodynamics. It is not the intent to replace wind tunnel or more rigorous analytical results, but rather to provide an efficient means of estimating vehicle aerodynamic characteristics and preliminary design stages. Thus, base on these preliminary design estimation, this project will assimillate the Utilization of Panel Method Using Fortran (a reliable and convenience way to represent linear equations and other listings through computer programs) to predict the aerodynamic sectional airfoil coefficients namely Cl (lift), Cd (drag) and Cm (moment) so as further analysis of aerodynamic characteristics can be done with the results obtained. NACA 0009 Symmetrical Airfoil and NACA 23018 Cambered Airfoil configuration is used as a comparable results with the one obtained from Abbot and Von Doenhoff Airfoil Data. Hopefully with this effort, those whose interest is Computational Aerodynamics, particularly with the use of Panel Method, will gain tremendously. To appreciate the PROGRAM PANEL is to really understand the gist of Panel Method. Enjoy reading.
format	Student Project
author	Abdullah, Abdul Rahman
author_facet	Abdullah, Abdul Rahman
author_sort	Abdullah, Abdul Rahman
title	Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah
title_short	Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah
title_full	Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah
title_fullStr	Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah
title_full_unstemmed	Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah
title_sort	fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain cl, cd & cm / abdul rahman abdullah
publisher	Faculty of Mechanical Engineering
publishDate	1999
url	http://ir.uitm.edu.my/id/eprint/25908/ http://ir.uitm.edu.my/id/eprint/25908/1/PPd_ABDUL%20RAHMAN%20ABDULLAH%20EM%2000_5.pdf
first_indexed	2023-09-18T23:15:45Z
last_indexed	2023-09-18T23:15:45Z
_version_	1777419099915157504

Fortran program utilizing panel method on arbitrary lifting airfoil in two-dimensional incompressible flow to obtain Cl, Cd & Cm / Abdul Rahman Abdullah

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