# 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
