# Create an array of alpha values. # In this case we create 6 evenly spaced values from 0 - 5. alphaList = np.linspace(0, 5, 6) # Create storage for the evaluated lift and drag coefficients CL = [] CD = [] # rst Start loop # Loop over the alpha values and evaluate the polar for alpha in alphaList: # rst update AP # Update the name in the AeroProblem. This allows us to modify the # output file names with the current alpha. ap.name = "wing_%4.2f" % alpha # Update the alpha in aero problem and print it to the screen. ap.alpha = alpha if comm.rank == 0: print("current alpha: %f" % ap.alpha) # rst Run ADflow # Solve the flow CFDSolver(ap) # Evaluate functions funcs = {} CFDSolver.evalFunctions(ap, funcs) # Store the function values in the output list
elif args.task == "polar": # Create an array of alpha values. # In this case we create 6 evenly spaced values from 0 - 5. alphaList = np.linspace(0, 5, 6) # Create storage for the evaluated lift and drag coefficients CLList = [] CDList = [] # rst Start loop # Loop over the alpha values and evaluate the polar for alpha in alphaList: # rst update AP # Update the name in the AeroProblem. This allows us to modify the # output file names with the current alpha. ap.name = f"wing_{alpha:4.2f}" # Update the alpha in aero problem and print it to the screen. ap.alpha = alpha if comm.rank == 0: print(f"current alpha: {ap.alpha}") # rst Run ADflow polar # Solve the flow CFDSolver(ap) # Evaluate functions funcs = {} CFDSolver.evalFunctions(ap, funcs) # Store the function values in the output list