Postprocessing for DU00-W-212: Coefficients of lift and drag

Angle of attack sweep

import yaml
import matplotlib.pyplot as plt
import numpy as np

size=14
params = {'legend.fontsize': 'large',
          'axes.labelsize': size,
          'axes.titlesize': size,
          'xtick.labelsize': size,
          'ytick.labelsize': size}
plt.rcParams.update(params)

# For website workflow
path_prefix = '../../nalu-wind/2D_airfoil_Transition/DU00-W-212/figures_and_scripts/'

re_list=[3]

n_re=len(re_list)

for i in range(n_re):
    re   = re_list[i]
    file =path_prefix+'../reference_data/exp_du00w212_re{:02d}M.yaml'.format(int(re))
    with open(file, "r") as data:
        clcd=yaml.safe_load(data)

    with open(path_prefix+'../performance/du00w212_F_rey{:08d}.yaml'.format(int(re*1e6)), "r") as data3:
        cfd_trans=yaml.safe_load(data3)

    with open(path_prefix+'../performance/du00w212_F_rey{:08d}_turb.yaml'.format(int(re*1e6)), "r") as data1:
        cfd_turb=yaml.safe_load(data1)


    plt.figure(figsize=(11,4))
    plt.subplot(1, 3, 1)
    plt.plot(clcd['DU00W212']['aoa'],clcd['DU00W212']['cl'],'ko')
    plt.plot(cfd_turb['du00w212_F']['aoa'],cfd_turb['du00w212_F']['cl'],'--')
    plt.plot(cfd_trans['du00w212_F']['aoa'],cfd_trans['du00w212_F']['cl'])
    plt.xlabel('Angle of Attack [deg]')
    plt.xlim([-10, 20])
    plt.ylim([-1, 2])
    plt.ylabel('Lift coefficient, $C_{l}$')
    plt.grid()
    plt.tight_layout() 
    plt.legend(['Experiment','Turbulent','Transition'])
    

    plt.subplot(1, 3, 2)
    plt.plot(clcd['DU00W212']['cd'],clcd['DU00W212']['cl'],'ko')
    plt.plot(cfd_turb['du00w212_F']['cd'],cfd_turb['du00w212_F']['cl'],'--')
    plt.plot(cfd_trans['du00w212_F']['cd'],cfd_trans['du00w212_F']['cl'])
    plt.xlabel('Drag coefficient, $C_{d}$')
    plt.ylabel('Lift coefficient, $C_{l}$')
    plt.xlim([0.0,0.03])
    plt.ylim([-1, 2])
    plt.grid()
    plt.tight_layout() 


    plt.subplot(1, 3, 3)
    plt.plot(clcd['DU00W212']['aoa'],clcd['DU00W212']['cm'],'ko')
    plt.plot(cfd_turb['du00w212_F']['aoa'],np.array(cfd_turb['du00w212_F']['cm'])*-1,'--')
    plt.plot(cfd_trans['du00w212_F']['aoa'],np.array(cfd_trans['du00w212_F']['cm'])*-1)
    plt.xlabel('Angle of Attack [deg]')
    plt.ylabel('Pitching moment coefficient, $C_{m}$')
    plt.xlim([-10, 20])
    plt.ylim([-0.12, -0.02])
    plt.grid()
    plt.tight_layout() 

    # plt.savefig("du_rey_%dM.png"%re,dpi=300)

plt.show()