GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 372 AIRFOIL (goe372-il) Reynolds number: 200,000 Max Cl/Cd: 82.49 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe372-il-200000.txt Download as CSV file: xf-goe372-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 372 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3608 0.08810 0.08497 -0.0343 1.0000 0.0384
-6.750 -0.3683 0.08345 0.08041 -0.0330 1.0000 0.0389
-6.500 -0.3719 0.08055 0.07755 -0.0284 1.0000 0.0397
-6.250 -0.3755 0.07863 0.07568 -0.0255 1.0000 0.0404
-6.000 -0.3799 0.07687 0.07396 -0.0233 1.0000 0.0412
-5.750 -0.3653 0.07367 0.07075 -0.0262 0.9977 0.0430
-5.500 -0.2980 0.06687 0.06371 -0.0488 0.9903 0.0500
-5.250 -0.2745 0.06039 0.05722 -0.0533 0.9855 0.0519
-5.000 -0.2460 0.05722 0.05402 -0.0557 0.9816 0.0552
-4.750 -0.1774 0.05091 0.04716 -0.0728 0.9740 0.0628
-4.500 -0.1559 0.04523 0.04155 -0.0752 0.9706 0.0651
-3.750 -0.0378 0.02946 0.02468 -0.0905 0.9567 0.0667
-3.500 -0.0055 0.02628 0.02112 -0.0924 0.9503 0.0694
-3.250 0.0326 0.02020 0.01378 -0.0945 0.9463 0.0642
-3.000 0.0717 0.01931 0.01287 -0.0972 0.9435 0.0699
-2.750 0.1057 0.01753 0.01064 -0.0982 0.9382 0.0718
-2.500 0.1418 0.01634 0.00909 -0.0996 0.9333 0.0749
-2.250 0.1800 0.01505 0.00761 -0.1016 0.9299 0.0791
-2.000 0.2117 0.01456 0.00709 -0.1023 0.9231 0.0864
-1.750 0.2464 0.01365 0.00609 -0.1034 0.9178 0.0944
-1.500 0.2793 0.01302 0.00547 -0.1042 0.9117 0.1088
-1.250 0.3104 0.01258 0.00505 -0.1047 0.9043 0.1249
-1.000 0.3409 0.01224 0.00472 -0.1050 0.8967 0.1396
-0.750 0.3716 0.01198 0.00445 -0.1054 0.8891 0.1583
-0.500 0.3989 0.01168 0.00424 -0.1051 0.8796 0.1767
-0.250 0.4281 0.01134 0.00398 -0.1051 0.8714 0.2013
0.000 0.4546 0.01089 0.00380 -0.1047 0.8616 0.2569
0.250 0.5010 0.00900 0.00364 -0.1086 0.8537 1.0000
0.500 0.5283 0.00904 0.00353 -0.1081 0.8433 1.0000
0.750 0.5553 0.00909 0.00345 -0.1075 0.8325 1.0000
1.000 0.5809 0.00917 0.00345 -0.1068 0.8201 1.0000
1.250 0.6065 0.00924 0.00346 -0.1060 0.8070 1.0000
1.500 0.6321 0.00932 0.00345 -0.1051 0.7931 1.0000
1.750 0.6575 0.00941 0.00347 -0.1043 0.7788 1.0000
2.000 0.6830 0.00950 0.00351 -0.1035 0.7644 1.0000
2.250 0.7084 0.00961 0.00357 -0.1027 0.7499 1.0000
2.500 0.7339 0.00973 0.00368 -0.1020 0.7354 1.0000
2.750 0.7583 0.00982 0.00376 -0.1010 0.7173 1.0000
3.000 0.7798 0.00978 0.00357 -0.0990 0.6818 1.0000
3.250 0.8020 0.00984 0.00354 -0.0974 0.6463 1.0000
3.500 0.8249 0.01000 0.00362 -0.0960 0.6132 1.0000
3.750 0.8464 0.01027 0.00371 -0.0944 0.5707 1.0000
4.000 0.8631 0.01087 0.00388 -0.0919 0.4935 1.0000
4.250 0.8785 0.01168 0.00417 -0.0895 0.3794 1.0000
4.500 0.8833 0.01389 0.00511 -0.0860 0.1583 1.0000
4.750 0.8955 0.01559 0.00615 -0.0835 0.0390 1.0000
5.000 0.9168 0.01632 0.00697 -0.0821 0.0332 1.0000
5.250 0.9380 0.01702 0.00784 -0.0808 0.0294 1.0000
5.500 0.9583 0.01782 0.00880 -0.0792 0.0280 1.0000
5.750 0.9765 0.01880 0.00991 -0.0774 0.0272 1.0000
6.000 0.9932 0.01994 0.01113 -0.0753 0.0270 1.0000
6.250 1.0095 0.02123 0.01248 -0.0732 0.0271 1.0000
6.500 1.0272 0.02272 0.01401 -0.0712 0.0278 1.0000
6.750 1.0490 0.02449 0.01586 -0.0697 0.0290 1.0000
7.000 1.0737 0.02629 0.01773 -0.0688 0.0290 1.0000
7.250 1.0999 0.02832 0.01988 -0.0681 0.0288 1.0000
7.500 1.1351 0.03212 0.02371 -0.0685 0.0332 1.0000
14.500 0.8087 0.17037 0.16742 -0.0809 0.0503 1.0000
14.750 0.8118 0.17360 0.17066 -0.0822 0.0472 1.0000
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Polar data table (+)
Polar graphs
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