There are various aircraft have already been built by using airfoil NACA 23018 as its wing cross section. Table Q1 below show the list of aircraft that use a NACA 23018, This airfoil has coordinates upper and lower surfaces are given by the following equation : Upper surface coordinates : And Lower surface coordinates : Where is the profile thickness distribution and is profile camber line distribution. These two functions are defined respectively as : and the camber line distribution : Where : The parameter Write the computer code in c with input will be key in is : - The number of point N distributed along x from x=0 to x=1. The output of the program will appear on the screen as below: - The maximum airfoil thickness = - The location of maximum airfoil camber line = - The number of point N=. The coordinate of profile wing aircraft