WingMotion.sweep = 15
WingMotion.dt = 0.001
WingMotion.run()
#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)
surface = WingSurface()
beam = BeamGeometryVT()
beam.x = np.array([0, 0.0, -0.05]);
beam.y = np.array([0, -0.01, -0.02]);
beam.z = np.array([0, 0.1, 0.2]);
beam.s = calculate_length(np.array([beam.x, beam.y, beam.z]).T)
beam.rot_x = [0, 0, 0];
beam.rot_y = [0, 0, 0];
beam.rot_z = [0, 0, 0];
surface.eqspar_geom = [beam]
planform = WingPlanformVT();
planform.blade_length = .2;
planform.chord = [1, 1, 0.5];
planform.rthick = np.array([0.05, 0.05, 0.05]);
planform.p_le = [0.0, 0.0, 0.0];
surface.planform_in = [planform];
surface.airfoils = [home+'/git/BISDEM/data/ffaw3241.dat', home+'/git/BISDEM/data/ffaw3301.dat'];
surface.span_ni = 3;
surface.run()
surf = surface.wingsurf
b = surf.blade_surface
surf.run()
pf = surf.pf_splines.pfOut
plt.figure()
plt.title('chord')
plt.plot(pf.s, pf.chord)