Information for "Development of a Generalized Source Code for NACA Four Digit Airfoils"

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Display titleDevelopment of a Generalized Source Code for NACA Four Digit Airfoils
Default sort keyDevelopment of a Generalized Source Code for NACA Four Digit Airfoils
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Page ID34812
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Page creatorRM (talk | contribs)
Date of page creation20:12, 12 May 2017
Latest editorRubiat Mustak (talk | contribs)
Date of latest edit13:23, 6 January 2018
Total number of edits4
Total number of distinct authors3
Recent number of edits (within past 90 days)0
Recent number of distinct authors0
Retrieved from "https://www.openresearch.org/wiki/Development_of_a_Generalized_Source_Code_for_NACA_Four_Digit_Airfoils"
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Has abstractAn airfoil is a cross section of airplanes …
An airfoil is a cross section of airplanes wings. It is very much difficult for a researcher to perform his test on the whole aircraft wing. So a test using small cross section of wings or airfoils is performed by researchers. For experimental purposes airfoils need to be constructed. For constructing a real airfoil model an airfoil profile is needed. For obtaining airfoil profiles coordinates are needed. There are many available online sources for these coordinates. But this study will show how someone can obtain required coordinates for drawing airfoil profile without taking any information from online available sources. For obtaining airfoil co ordinates generalized equations for airfoils are used. The whole coordinate generation is performed using programming languages. In this case C programming is used. With the help of these co ordinates generated by c programming it is possible to draw airfoil profiles hence an airfoil profile for NACA-4415 airfoil is also shown. The whole study is based on NACA four digit airfoils. In the same fashion study based on NACA five digit and NACA Six digit can be performed.
digit and NACA Six digit can be performed. +
Has authorsRubiat Mustak +
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TitleDevelopment of a Generalized Source Code for NACA Four Digit Airfoils +
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