GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 50,000 Max Cl/Cd: 40.52 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe442-il-50000-n5.txt Download as CSV file: xf-goe442-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3391 0.09807 0.09152 -0.0233 1.0000 0.0899
-7.250 -0.3467 0.09645 0.09003 -0.0236 1.0000 0.0926
-7.000 -0.3544 0.09519 0.08890 -0.0274 1.0000 0.0944
-6.750 -0.3502 0.09127 0.08507 -0.0257 1.0000 0.0964
-6.500 -0.3437 0.08811 0.08196 -0.0230 1.0000 0.1007
-6.250 -0.3423 0.08565 0.07957 -0.0238 1.0000 0.1051
-6.000 -0.3406 0.08393 0.07786 -0.0323 1.0000 0.1093
-5.750 -0.3363 0.07986 0.07390 -0.0267 1.0000 0.1119
-5.500 -0.3303 0.07692 0.07100 -0.0258 1.0000 0.1148
-5.250 -0.3227 0.07396 0.06806 -0.0269 1.0000 0.1181
-5.000 -0.2983 0.06646 0.06030 -0.0346 1.0000 0.0639
-4.750 -0.2856 0.06267 0.05646 -0.0358 1.0000 0.0604
-4.500 -0.2683 0.05860 0.05228 -0.0384 1.0000 0.0587
-4.250 -0.2491 0.05480 0.04833 -0.0407 1.0000 0.0594
-4.000 -0.2278 0.05100 0.04434 -0.0430 1.0000 0.0600
-3.750 -0.2039 0.04696 0.04000 -0.0454 1.0000 0.0594
-3.500 -0.1783 0.04304 0.03572 -0.0474 1.0000 0.0589
-3.250 -0.1526 0.03974 0.03202 -0.0489 1.0000 0.0609
-3.000 -0.1248 0.03665 0.02834 -0.0502 1.0000 0.0645
-2.750 -0.0870 0.03347 0.02432 -0.0527 0.9965 0.0666
-2.500 -0.0471 0.03128 0.02194 -0.0561 0.9885 0.0734
-2.250 -0.0038 0.02912 0.01901 -0.0589 0.9803 0.0795
-2.000 0.0365 0.02758 0.01721 -0.0617 0.9709 0.0888
-1.750 0.0789 0.02620 0.01529 -0.0640 0.9611 0.0951
-1.500 0.1196 0.02514 0.01409 -0.0665 0.9506 0.1046
-1.250 0.1617 0.02427 0.01302 -0.0689 0.9390 0.1149
-1.000 0.2020 0.02356 0.01205 -0.0708 0.9259 0.1240
-0.750 0.2413 0.02289 0.01142 -0.0728 0.9120 0.1428
-0.250 0.3201 0.02112 0.01037 -0.0767 0.8830 0.3047
0.000 0.3650 0.01912 0.00980 -0.0791 0.8687 1.0000
0.500 0.4376 0.01894 0.00902 -0.0810 0.8312 1.0000
0.750 0.4730 0.01885 0.00871 -0.0817 0.8109 1.0000
1.000 0.5082 0.01878 0.00843 -0.0824 0.7903 1.0000
1.250 0.5412 0.01876 0.00824 -0.0827 0.7676 1.0000
1.500 0.5753 0.01875 0.00804 -0.0831 0.7460 1.0000
1.750 0.6059 0.01886 0.00798 -0.0830 0.7228 1.0000
2.000 0.6372 0.01897 0.00792 -0.0830 0.7015 1.0000
2.250 0.6651 0.01921 0.00804 -0.0826 0.6792 1.0000
2.500 0.6938 0.01947 0.00814 -0.0823 0.6594 1.0000
2.750 0.7213 0.01978 0.00832 -0.0818 0.6403 1.0000
3.000 0.7479 0.02013 0.00861 -0.0813 0.6222 1.0000
3.250 0.7746 0.02051 0.00891 -0.0808 0.6051 1.0000
3.500 0.8011 0.02092 0.00925 -0.0803 0.5892 1.0000
3.750 0.8274 0.02135 0.00965 -0.0798 0.5736 1.0000
4.000 0.8529 0.02177 0.01001 -0.0791 0.5565 1.0000
4.250 0.8774 0.02218 0.01032 -0.0781 0.5365 1.0000
4.500 0.8991 0.02261 0.01072 -0.0767 0.5135 1.0000
4.750 0.9217 0.02302 0.01103 -0.0754 0.4918 1.0000
5.000 0.9428 0.02349 0.01153 -0.0741 0.4714 1.0000
5.250 0.9653 0.02397 0.01206 -0.0730 0.4544 1.0000
5.500 0.9873 0.02445 0.01263 -0.0719 0.4372 1.0000
5.750 1.0090 0.02493 0.01318 -0.0707 0.4201 1.0000
6.000 1.0305 0.02543 0.01376 -0.0695 0.4032 1.0000
6.250 1.0510 0.02595 0.01440 -0.0682 0.3849 1.0000
6.500 1.0704 0.02651 0.01507 -0.0667 0.3646 1.0000
6.750 1.0893 0.02708 0.01567 -0.0651 0.3439 1.0000
7.000 1.1076 0.02776 0.01642 -0.0636 0.3220 1.0000
7.250 1.1257 0.02851 0.01721 -0.0620 0.3013 1.0000
7.500 1.1442 0.02936 0.01811 -0.0606 0.2835 1.0000
7.750 1.1629 0.03032 0.01913 -0.0592 0.2670 1.0000
8.000 1.1814 0.03132 0.02019 -0.0579 0.2529 1.0000
8.250 1.1999 0.03237 0.02132 -0.0566 0.2406 1.0000
8.500 1.2184 0.03350 0.02260 -0.0554 0.2296 1.0000
8.750 1.2379 0.03468 0.02396 -0.0543 0.2214 1.0000
9.000 1.2575 0.03592 0.02538 -0.0532 0.2143 1.0000
9.250 1.2768 0.03724 0.02688 -0.0522 0.2076 1.0000
9.500 1.2943 0.03859 0.02846 -0.0509 0.2006 1.0000
9.750 1.3126 0.03999 0.03003 -0.0498 0.1945 1.0000
10.000 1.3280 0.04162 0.03201 -0.0484 0.1884 1.0000
10.250 1.3458 0.04298 0.03353 -0.0473 0.1817 1.0000
10.500 1.3527 0.04462 0.03554 -0.0450 0.1734 1.0000
10.750 1.3567 0.04599 0.03708 -0.0425 0.1633 1.0000
11.000 1.3547 0.04711 0.03825 -0.0395 0.1520 1.0000
11.250 1.3477 0.04833 0.03948 -0.0361 0.1412 1.0000
11.500 1.3347 0.05055 0.04202 -0.0330 0.1325 1.0000
11.750 1.3257 0.05264 0.04417 -0.0308 0.1238 1.0000
12.000 1.3144 0.05552 0.04734 -0.0293 0.1160 1.0000
12.250 1.3038 0.05866 0.05062 -0.0284 0.1087 1.0000
12.500 1.2903 0.06262 0.05484 -0.0285 0.1013 1.0000
12.750 1.2773 0.06695 0.05934 -0.0292 0.0945 1.0000
13.000 1.2628 0.07207 0.06470 -0.0306 0.0877 1.0000
13.250 1.2484 0.07754 0.07034 -0.0326 0.0817 1.0000
13.500 1.2324 0.08376 0.07677 -0.0352 0.0761 1.0000
13.750 1.2192 0.08957 0.08265 -0.0377 0.0714 1.0000
14.000 1.1999 0.09716 0.09048 -0.0412 0.0685 1.0000
14.250 1.1803 0.10513 0.09862 -0.0450 0.0667 1.0000
14.500 1.1546 0.11503 0.10868 -0.0500 0.0670 1.0000
14.750 1.1216 0.12758 0.12130 -0.0566 0.0694 1.0000
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Polar data table (+)
Polar graphs
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