interpolate_naca_camber

Interpolate aerofoil camber at non-dimensional coordinate eta in (0,1), where (M00,P00) and (M01,P01) define the camber properties at eta=0 and eta=1 respectively.

Notes

For two surfaces, eta can be in (-1,1). In this case, the root is eta=0 and the tips are at eta=+-1.