nathanrooy/aerodynamic-shape-optimization

Python scripts related to aerodynamic analysis and shape optimization

aerodynamic-shape-optimization's Issues

Error during the optimisation

While running opt = sa.minimize(cost_function, res.x, opt_mode = 'continuous', step_max=500, t_max=2.5, t_min=0, damping=0.01). The code does not estimate the cl/cd value for the new airfoil. The following are the output:

cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235
cl/cd=0.3166 -> cost_func=3158.8235

And on the terminal the following error raises:

Fortran runtime error: End of file

'rm' is not recognized as an internal or external command, operable program or batch file.

Is it due to the Xfoil or am I doing something wrong here?

Please clarify.

Error while running the notebook

The following error appears while running the cell contains minimize function res = minimize(shape_match, initial_airfoil, method='Powell', tol=1e-10, options={'disp': True, 'maxiter':10000})

Input In [19], in shape_match(control_pts, xpts, ta)
3 def shape_match(control_pts, xpts=xpts, ta=target_airfoil):
----> 4 ca = np.array(bezier_airfoil(xpts, munge_ctlpts(control_pts, 3, 3)))
5 try:
6 return 1000 * np.sum(abs(ca[:,0] - ta[:,0]) + abs(ca[:,1] - ta[:,1]))

NameError: name 'bezier_airfoil' is not defined

Please clarify. Thanks.