S2062 8% (s2062-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2062 8% (s2062-il) Reynolds number: 500,000 Max Cl/Cd: 89.26 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2062-il-500000.txt Download as CSV file: xf-s2062-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S2062 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.2560 0.00524 0.00164 -0.0536 0.8604 0.9464
0.500 0.2885 0.00523 0.00159 -0.0543 0.8471 0.9660
0.750 0.3257 0.00523 0.00155 -0.0561 0.8329 0.9815
1.000 0.3655 0.00524 0.00150 -0.0586 0.8171 0.9929
1.250 0.3993 0.00527 0.00147 -0.0598 0.7984 1.0000
1.500 0.4221 0.00534 0.00146 -0.0587 0.7771 1.0000
1.750 0.4457 0.00543 0.00147 -0.0577 0.7537 1.0000
2.000 0.4698 0.00555 0.00151 -0.0568 0.7269 1.0000
2.250 0.4942 0.00570 0.00155 -0.0560 0.6969 1.0000
2.500 0.5188 0.00589 0.00161 -0.0553 0.6646 1.0000
2.750 0.5433 0.00610 0.00169 -0.0545 0.6295 1.0000
3.000 0.5677 0.00636 0.00179 -0.0538 0.5894 1.0000
3.250 0.5907 0.00674 0.00194 -0.0528 0.5282 1.0000
3.500 0.6135 0.00719 0.00211 -0.0519 0.4617 1.0000
3.750 0.6378 0.00757 0.00230 -0.0513 0.4116 1.0000
4.000 0.6612 0.00807 0.00252 -0.0506 0.3503 1.0000
4.250 0.6841 0.00866 0.00281 -0.0499 0.2787 1.0000
4.500 0.7082 0.00915 0.00308 -0.0494 0.2283 1.0000
4.750 0.7319 0.00970 0.00340 -0.0489 0.1756 1.0000
5.000 0.7549 0.01037 0.00379 -0.0483 0.1180 1.0000
5.250 0.7752 0.01147 0.00444 -0.0472 0.0394 1.0000
5.500 0.7991 0.01210 0.00502 -0.0465 0.0254 1.0000
5.750 0.8230 0.01273 0.00569 -0.0458 0.0214 1.0000
6.000 0.8466 0.01339 0.00644 -0.0450 0.0201 1.0000
6.250 0.8703 0.01400 0.00714 -0.0442 0.0194 1.0000
6.500 0.8932 0.01471 0.00796 -0.0434 0.0186 1.0000
6.750 0.9154 0.01554 0.00887 -0.0424 0.0179 1.0000
7.000 0.9370 0.01647 0.00989 -0.0413 0.0172 1.0000
7.250 0.9589 0.01735 0.01083 -0.0404 0.0163 1.0000
7.500 0.9799 0.01839 0.01194 -0.0394 0.0154 1.0000
7.750 0.9999 0.01983 0.01348 -0.0382 0.0150 1.0000
8.000 1.0194 0.02177 0.01558 -0.0370 0.0146 1.0000
8.250 1.0386 0.02433 0.01834 -0.0357 0.0143 1.0000
8.500 1.0566 0.02734 0.02163 -0.0344 0.0142 1.0000
8.750 1.0690 0.03142 0.02611 -0.0325 0.0140 1.0000
9.000 1.0917 0.03043 0.02526 -0.0316 0.0131 1.0000
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Polar data table (+)
Polar graphs
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