transform module

class transform.TransformBlade(M_yaml, b_yaml, b_pitch, M, b)

Bases: object

calc_M_b_total(eta)

grassmann_to_nominal(xy_gr, eta)

grassmann_to_phys(xy_gr, eta)

make_R_out_interpolator(eta)

Airfoils shapes have to be rotated out of xy plane to be normal to y component (in local coord) of ref axis (elastic axis).

Parameters:

eta – locations along the blade span (need to define the range)

Returns:

rotation interpolator

update_M_yaml_interpolator(x_twist, twist, x_chord, chordx, chordy)

transform.global_blade_coordinates(xyz_local)

transform.transform_blade_for_BEM(eta_span, shapes, twist, scalex, scaley, pitch)

Parameters:

• eta_span – locations of cross sections on (0, 1)

• shapes – grassmann shapes

• twist – twist interpolator

• scalex – chord interpolator (should be the same as scaley)

• scaley – chord interpolator

• pitch – pitch interpolator

Returns:

transform.transform_for_BEM(eta, xy, twist, scalex, scaley, pitch)