Esempio n. 1
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"""
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()
Esempio n. 2
0
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];