GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 441 AIRFOIL (goe441-il) Reynolds number: 50,000 Max Cl/Cd: 31 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe441-il-50000-n5.txt Download as CSV file: xf-goe441-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 441 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 0.0369 0.11190 0.10501 -0.0890 0.8936 0.1350
-8.000 0.0435 0.10965 0.10275 -0.0934 0.8863 0.1359
-7.750 0.0405 0.10809 0.10124 -0.0935 0.8732 0.1361
-7.500 0.0728 0.10277 0.09588 -0.0955 0.8689 0.1376
-7.250 0.0864 0.10006 0.09319 -0.0945 0.8574 0.1406
-6.250 0.0988 0.08661 0.07962 -0.1016 0.8146 0.0964
-6.000 0.1028 0.08427 0.07729 -0.1013 0.8011 0.0943
-5.750 0.1114 0.08088 0.07387 -0.1039 0.7905 0.0918
-5.500 0.1174 0.07559 0.06850 -0.1113 0.7789 0.0881
-5.250 0.1272 0.07251 0.06539 -0.1137 0.7656 0.0879
-5.000 0.1541 0.06758 0.06034 -0.1209 0.7581 0.0887
-4.750 0.1659 0.06580 0.05855 -0.1209 0.7440 0.0900
-4.500 0.1928 0.06146 0.05408 -0.1272 0.7342 0.0908
-4.250 0.2252 0.05552 0.04788 -0.1369 0.7232 0.0908
-4.000 0.2635 0.05028 0.04229 -0.1460 0.7129 0.0921
-3.750 0.3204 0.04373 0.03496 -0.1596 0.7037 0.0972
-3.500 0.3575 0.04112 0.03200 -0.1639 0.6932 0.1005
-3.250 0.3960 0.03903 0.02956 -0.1675 0.6838 0.1050
-3.000 0.4339 0.03694 0.02695 -0.1712 0.6733 0.1116
-2.750 0.4685 0.03577 0.02557 -0.1730 0.6647 0.1179
-2.500 0.4997 0.03476 0.02426 -0.1744 0.6545 0.1256
-2.250 0.5352 0.03374 0.02287 -0.1761 0.6465 0.1357
-2.000 0.5612 0.03344 0.02258 -0.1762 0.6374 0.1438
-1.750 0.5930 0.03288 0.02183 -0.1771 0.6297 0.1551
-1.500 0.6238 0.03250 0.02125 -0.1778 0.6224 0.1679
-1.250 0.6524 0.03232 0.02088 -0.1782 0.6146 0.1814
-1.000 0.6874 0.03182 0.02016 -0.1792 0.6092 0.1972
-0.750 0.7104 0.03196 0.02033 -0.1789 0.6010 0.2102
-0.500 0.7417 0.03170 0.01993 -0.1795 0.5952 0.2264
-0.250 0.7742 0.03143 0.01953 -0.1802 0.5900 0.2453
0.000 0.7983 0.03166 0.01979 -0.1800 0.5832 0.2642
0.250 0.8295 0.03153 0.01964 -0.1806 0.5779 0.2936
0.500 0.8638 0.03129 0.01945 -0.1814 0.5736 0.3346
0.750 0.8836 0.03191 0.02027 -0.1806 0.5669 0.3806
1.000 0.9108 0.03216 0.02059 -0.1805 0.5618 0.4427
1.250 0.9422 0.03219 0.02059 -0.1807 0.5577 0.5080
1.750 0.9808 0.03322 0.02197 -0.1780 0.5472 0.6335
2.000 1.0019 0.03333 0.02224 -0.1765 0.5427 0.7129
2.250 1.0211 0.03295 0.02204 -0.1741 0.5392 0.8425
2.500 1.0435 0.03379 0.02272 -0.1739 0.5343 1.0000
2.750 1.0608 0.03504 0.02389 -0.1732 0.5287 1.0000
3.000 1.0873 0.03577 0.02443 -0.1734 0.5241 1.0000
3.250 1.1205 0.03615 0.02456 -0.1743 0.5204 1.0000
3.500 1.1446 0.03704 0.02531 -0.1741 0.5163 1.0000
3.750 1.1467 0.03905 0.02742 -0.1715 0.5102 1.0000
4.000 1.1654 0.04017 0.02847 -0.1708 0.5055 1.0000
4.250 1.1954 0.04067 0.02881 -0.1711 0.5018 1.0000
4.500 1.2327 0.04084 0.02878 -0.1724 0.4989 1.0000
4.750 1.2044 0.04457 0.03280 -0.1666 0.4914 1.0000
5.000 1.2028 0.04679 0.03506 -0.1637 0.4858 1.0000
5.250 1.2297 0.04740 0.03557 -0.1637 0.4823 1.0000
5.500 1.2708 0.04729 0.03531 -0.1651 0.4796 1.0000
5.750 1.1550 0.05829 0.04684 -0.1543 0.4654 1.0000
6.000 1.1799 0.05886 0.04733 -0.1539 0.4623 1.0000
6.250 1.2168 0.05837 0.04673 -0.1541 0.4602 1.0000
8.750 1.0872 0.10779 0.09684 -0.1461 0.3867 1.0000
9.000 1.0530 0.11594 0.10511 -0.1469 0.3761 1.0000
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Polar data table (+)
Polar graphs
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