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]