ParametricAirfoils.jl

using ParametricAirfoils, AirfoilDatabase
########## STEP 1. Select a parameterization method ##########
# 1.1. CST Method
    N = 9 # num of params for **EACH** curve
    cst = CST(N) # == CST(N, Float64; N1=0.5, N2=1)
    csts = CST(N; link_le=false) # Different `A0` for upper and lower surfaces, **NOT recommended**
# 1.2. Mean Camber + Thickness (MCT)
    # 1.2.1 CST(mean-camber) + CST(half-thicness)
    mctcc = MCT(CurveCST(N, 1, 1, Float64), CurveCST(N, 0.5, 1.0, Float64))
    # 1.2.2 CST(mean-camber) + polynomial(half-thicness)
    indicies = tuple((max(0.5, i-1) for i in 1:N)...) # poly nomial indicies
    mctcp = MCT(CurveCST(N, 1, 1, Float64), CurvePoly(indicies, Float64))
    # 1.2.3 More curve types can be derived from `CurveFunction`, see `src/curve/_init.jl`
########## STEP 2. Create ParametricAirfoil ##########
# 2.1. Fitting airfoil data
    # install AirfoilDatabase.jl
    # run in REPL: `] add AirfoilDatabase`
    result = query_airfoil("N0012")
    @assert length(result)==1
    NACA0012 = result[1]
    airfoil, fiterr = fit(cst, NACA0012.x, NACA0012.y)
    # `cst` can be replaced with any parameterization method
# 2.2. Create from parameters
    param = get_param(airfoil) # any vector of length `num_param(cst)`
    airfoil2 = ParametricAirfoil(cst, param)
########## STEP 3. Airfoil Coordinates ##########
    xm = LinRange(0, 1, 33)
    yu = airfoil(:U, xm) # Upper side
    yl = airfoil(:L, xm) # Lower side
    # OR with gradient information
    yu, dyu =  airfoil(:U, xm, true)
    # OR generate points at once for meshing 
    x, y = gen_airfoil(airfoil)