The cross section of an aircraft wing is a shape known as an air foil. Air foil design requires a sophisticated knowledge of aerodynamics; however, there are a large number of standard air foils that can be used in aerodynamic design. These standard air foils are generally defined by x-y coordinates, non-dimensional zed such that the tip of the air foil is at the point (0,0) and the tail of the air foil is at the point (1,0).
Locate and download the coordinate points that define the Selig 1223 air foil. A good database for this is the UIUC Air foil Coordinate Database (available at http://www.ae.uiuc.edu/m-selig/ads/coord_database.html). While the coordinates are non-dimensional, and can be scaled for any unit system, assume that in this case the units of the coordinates are meters.
a. Using Excel, plot the air foil coordinates to see the shape of the air foil (be sure to scale the plot such that the scales on the x- and y-axes are identical, so the air foil shape will appear correct).
b. Using Excel, perform numerical integration to determine the cross-sectional area of the air foil
