wing1.addLiftingSurface(1, x1, x2, x3, x4, nspan, nchord)
# Make a FEM model
model = Model()
model.addAircraftParts([wing1])
# Apply the constraint for the model
model.applyConstraints(0, 'fix')
model.plotRigidModel(numXSects=10)
# Aerodynamic Model Validation
M = .24
kr = .47
b = .4572 / 2
model.calcAIC(M, kr, b, symxz=True)
model.normalModesAnalysis()
pbar = np.dot(
np.linalg.inv(model.D),
np.dot(model.W, -model.umode[:, 0] / max(abs(model.umode[:, 0]))))
pbarReal = np.real(pbar)
pbarImag = np.imag(pbar)
pbarPlot = pbar[330:330 + 10]
#pbarPlot = pbar[0:0+10]
xs = np.zeros((10))
for i in range(0, 10):
xs[i] = model.aeroBox[i].Xr[0]
wing1.addLiftingSurface(1,x1,x2,x3,x4,nspan,nchord)
# Make a FEM model
model = Model()
model.addAircraftParts([wing1])
# Apply the constraint for the model
model.applyConstraints(0,'fix')
model.plotRigidModel(numXSects=10)
# Aerodynamic Model Validation
M = .24
kr = .47
b = .4572/2
model.calcAIC(M,kr,b,symxz=True)
model.normalModesAnalysis()
pbar = np.dot(np.linalg.inv(model.D),np.dot(model.W,-model.umode[:,0]/max(abs(model.umode[:,0]))))
pbarReal = np.real(pbar)
pbarImag = np.imag(pbar)
pbarPlot = pbar[330:330+10]
#pbarPlot = pbar[0:0+10]
xs = np.zeros((10))
for i in range(0,10):
xs[i] = model.aeroBox[i].Xr[0]
xs = xs/c-.05
nchord = 10
wing1.addLiftingSurface(1,x1,x2,x3,x4,nspan,nchord)
# Make a FEM model
model = Model()
model.addAircraftParts([wing1])
# Apply the constraint for the model
model.applyConstraints(0,'fix')
model.plotRigidModel(numXSects=10)
model.normalModesAnalysis()
freqs = model.freqs
'''
# Aerodynamic Model Validation
model.calcAIC(.24,.47,.4572/2,symxz=True)
model.normalModesAnalysis()
pbar = np.dot(np.linalg.inv(model.D),np.dot(model.W,-model.umode[:,0]/max(abs(model.umode[:,0]))))
pbarReal = np.real(pbar)
pbarImag = np.imag(pbar)
pbarPlot = pbar[330:330+10]
#pbarPlot = pbar[0:0+10]
xs = np.zeros((10))
for i in range(0,10):
xs[i] = model.aeroBox[i].Xr[0]
