#mechanimation2D(MechMotion.mpos.front,WingMotion.wpos.front, 20)
#mechplot2D(MechMotion.mpos,WingMotion.wpos,2)
surface = WingSurface()
surface.eqspar_geom = WingMotion.wpos.eqspar_geom
planform = WingPlanformVT();
planform.blade_length = .2;
planform.chord = np.ones(10)*0.22
planform.chord = np.append(planform.chord, np.linspace(.220, .0860254, 20))
planform.rthick = np.ones(30)*0.16
planform.p_le = np.zeros(30)
surface.planform_in = [planform]*len(WingMotion.wpos.eqspar_geom);
surface.airfoils = [home+'/git/BISDEM/data/s8037.dat', home+'/git/BISDEM/data/s8037.dat'];
surface.span_ni = 30
surface.run()
fig = plt.figure()
ax = fig.add_subplot(111, projection='3d')
ax.set_aspect('equal')
ax.set_xlim(-0.1, 1.4)
ax.set_ylim(-0.5, 1.0)
ax.set_zlim(-0.5, 1.0)
ax.view_init(18, -133)
# Initialize
lines = []
blades = []
for index in range(surface.wingsurf[0].blade_surface.span_ni):
