#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): lobj = ax.plot([],[],[],"r",lw=2)[0] lines.append(lobj)