Table 7 Comparison of force components for a NACA 0012 airfoil at \(\alpha =5^{\circ }\), \(10^{\circ }\), and \(14^{\circ }\) with BC-3 (columns two to five), PVBC (last four columns), and different domain sizes

\(\alpha =5^{\circ }\)

    500

0.00902

0.00229

0.00673

0.54905

-

-

-

-

    300

0.00903

0.00230

0.00673

0.54895

-

-

-

-

    100

0.00907

0.00234

0.00673

0.54849

-

-

-

-

    50

0.00913

0.00240

0.00673

0.54778

0.00901

0.00228

0.00673

0.54924

    30

0.00922

0.00248

0.00674

0.54686

0.00901

0.00228

0.00673

0.54926

    10

0.00963

0.00289

0.00674

0.54267

0.00902

0.00228

0.00674

0.54959

    5

0.01025

0.00349

0.00676

0.53743

0.00904

0.00229

0.00675

0.55051

    3

0.01109

0.00430

0.00679

0.53182

0.00910

0.00233

0.00677

0.55236

\(\alpha =10^{\circ }\)

    500

0.01219

0.00590

0.00629

1.07648

-

-

-

-

    300

0.01223

0.00594

0.00629

1.07633

-

-

-

-

    100

0.01239

0.00609

0.00629

1.07550

-

-

-

-

    50

0.01262

0.00633

0.00629

1.07424

0.01215

0.00586

0.00629

1.07687

    30

0.01294

0.00664

0.00630

1.07273

0.01215

0.00586

0.00629

1.07708

    10

0.01449

0.00817

0.00631

1.06529

0.01216

0.00586

0.00629

1.07767

    5

0.01680

0.01045

0.00634

1.05672

0.01219

0.00588

0.00631

1.07981

    3

0.01990

0.01351

0.00640

1.04820

0.01228

0.00595

0.00633

1.08377

\(\alpha =14^{\circ }\)

    500

0.01802

0.01239

0.00563

1.45162

-

-

-

-

    300

0.01807

0.01245

0.00563

1.45142

-

-

-

-

    100

0.01835

0.01272

0.00563

1.45048

-

-

-

-

    50

0.01877

0.01313

0.00563

1.44910

0.01794

0.01231

0.00563

1.45210

    30

0.01932

0.01368

0.00564

1.44733

0.01794

0.01231

0.00563

1.45227

    10

0.02206

0.01639

0.00567

1.43952

0.01795

0.01231

0.00563

1.45333

    5

0.02617

0.02045

0.00572

1.43164

0.01798

0.01234

0.00564

1.45671

    3

0.03178

0.02597

0.00581

1.42590

0.01810

0.01243

0.00567

1.46306