Easy-to-use airfoil database from UIUC.
# import the package
using AirfoilDatabase
# query from database
result = query_airfoil("RAE 2822")
@assert length(result) == 1
airfoil = result[1]
@show airfoil.name
@show airfoil.desc
@show airfoil.x # x-coordinates
@show airfoil.y # y-coordinates
#4-digit NACA airfoil
np = 65 # num of points on each side, including the leading edge point
airfoil = NACA("0012", np) # optinal kwarg: sharpTE=true for zero-thick trailing edge
# specify the chordwise distribution
x = LinRange(0, 1, 33)
airfoil = NACA("2412", x; sharpTE=true)