Development of a Generalized Source Code for NACA Four Digit Airfoils

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 four digit can be performed.