""" WingMotion = wing_motion() # Hand over definition and positions of mechanism WingMotion.wdef = WingInit.wdef WingMotion.mpos = MechMotion.mpos WingMotion.n = 30 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()
import numpy as np
import matplotlib.pyplot as plt
from BISDEM.WingSE.wingsurface import WingSurface
from BISDEM.lib.vartrees import WingPlanformVT
from openmdao.main.api import Component
from openmdao.lib.datatypes.api import Float, List, Slot, File, FileRef
from fusedwind.turbine.geometry_vt import BeamGeometryVT, BladePlanformVT
from fusedwind.lib.geom_tools import calculate_length
from os.path import expanduser
home = expanduser("~")
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];