GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 622 AIRFOIL (goe622-il) Reynolds number: 50,000 Max Cl/Cd: 35.5 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe622-il-50000.txt Download as CSV file: xf-goe622-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 622 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4753 0.09690 0.09023 -0.0042 1.0000 0.2433
-7.500 -0.4738 0.09359 0.08700 -0.0044 1.0000 0.2540
-7.250 -0.4786 0.09082 0.08434 -0.0051 1.0000 0.2656
-6.750 -0.4681 0.08405 0.07765 -0.0042 1.0000 0.2962
-6.500 -0.4627 0.08088 0.07454 -0.0034 1.0000 0.3155
-6.250 -0.4616 0.07783 0.07157 -0.0029 1.0000 0.3378
-6.000 -0.4512 0.07471 0.06849 0.0006 1.0000 0.3699
-5.750 -0.4551 0.07268 0.06656 0.0025 1.0000 0.4065
-5.500 -0.4365 0.06888 0.06276 0.0077 1.0000 0.4420
-5.250 -0.4287 0.06601 0.05995 0.0120 1.0000 0.4836
-5.000 -0.4175 0.05414 0.04756 -0.0273 1.0000 0.2655
-4.750 -0.3729 0.04152 0.03325 -0.0405 1.0000 0.1458
-4.500 -0.3515 0.03762 0.02892 -0.0405 1.0000 0.1428
-4.250 -0.3282 0.03446 0.02500 -0.0404 1.0000 0.1478
-4.000 -0.3063 0.03176 0.02215 -0.0397 1.0000 0.1549
-3.750 -0.2814 0.02925 0.01909 -0.0391 1.0000 0.1645
-3.500 -0.2573 0.02726 0.01684 -0.0384 1.0000 0.1794
-3.250 -0.2325 0.02542 0.01480 -0.0377 1.0000 0.1969
-3.000 -0.2074 0.02383 0.01306 -0.0370 1.0000 0.2230
-2.750 -0.1822 0.02238 0.01164 -0.0362 1.0000 0.2578
-2.500 -0.1562 0.02112 0.01042 -0.0355 1.0000 0.3064
-2.250 -0.1304 0.01987 0.00952 -0.0350 1.0000 0.3733
-2.000 -0.1071 0.01782 0.00867 -0.0336 1.0000 0.5404
-1.750 -0.0707 0.01635 0.00779 -0.0326 1.0000 1.0000
-1.500 -0.0493 0.01648 0.00748 -0.0318 1.0000 1.0000
-1.250 -0.0281 0.01664 0.00731 -0.0311 1.0000 1.0000
-1.000 -0.0069 0.01684 0.00720 -0.0305 1.0000 1.0000
-0.750 0.0142 0.01707 0.00721 -0.0299 1.0000 1.0000
-0.500 0.0351 0.01736 0.00729 -0.0294 1.0000 1.0000
-0.250 0.0558 0.01769 0.00746 -0.0290 1.0000 1.0000
0.000 0.0763 0.01808 0.00768 -0.0287 1.0000 1.0000
0.250 0.0964 0.01853 0.00801 -0.0284 1.0000 1.0000
0.500 0.1160 0.01904 0.00843 -0.0283 1.0000 1.0000
0.750 0.1353 0.01963 0.00893 -0.0282 1.0000 1.0000
1.000 0.1542 0.02029 0.00953 -0.0282 1.0000 1.0000
1.250 0.1727 0.02102 0.01019 -0.0283 1.0000 1.0000
1.500 0.1911 0.02181 0.01095 -0.0285 1.0000 1.0000
1.750 0.2092 0.02266 0.01177 -0.0287 1.0000 1.0000
2.000 0.2598 0.02378 0.01290 -0.0350 0.9857 1.0000
2.250 0.3163 0.02480 0.01398 -0.0419 0.9660 1.0000
2.500 0.3734 0.02565 0.01492 -0.0485 0.9451 1.0000
2.750 0.4238 0.02632 0.01573 -0.0534 0.9227 1.0000
3.000 0.4816 0.02677 0.01636 -0.0591 0.9012 1.0000
3.250 0.5237 0.02719 0.01695 -0.0617 0.8776 1.0000
3.500 0.5767 0.02729 0.01733 -0.0655 0.8557 1.0000
3.750 0.6196 0.02730 0.01757 -0.0671 0.8318 1.0000
4.000 0.6600 0.02700 0.01751 -0.0674 0.8048 1.0000
4.250 0.7019 0.02598 0.01677 -0.0662 0.7741 1.0000
4.500 0.7333 0.02512 0.01608 -0.0634 0.7398 1.0000
4.750 0.7629 0.02442 0.01555 -0.0606 0.7059 1.0000
5.000 0.7904 0.02396 0.01525 -0.0576 0.6697 1.0000
5.250 0.8163 0.02373 0.01506 -0.0546 0.6283 1.0000
5.500 0.8392 0.02383 0.01514 -0.0514 0.5787 1.0000
5.750 0.8606 0.02424 0.01543 -0.0482 0.5237 1.0000
6.000 0.8810 0.02489 0.01592 -0.0453 0.4671 1.0000
6.250 0.8997 0.02549 0.01635 -0.0425 0.4122 1.0000
6.500 0.9194 0.02641 0.01705 -0.0402 0.3645 1.0000
6.750 0.9391 0.02767 0.01809 -0.0382 0.3205 1.0000
7.000 0.9522 0.02884 0.01906 -0.0357 0.2676 1.0000
7.250 0.9597 0.03015 0.02000 -0.0328 0.2079 1.0000
7.500 0.9718 0.03305 0.02251 -0.0300 0.1490 1.0000
7.750 0.9910 0.03603 0.02544 -0.0284 0.1194 1.0000
8.000 1.0141 0.03931 0.02889 -0.0271 0.1061 1.0000
8.250 1.0373 0.04271 0.03237 -0.0263 0.0983 1.0000
8.500 1.0519 0.04639 0.03671 -0.0244 0.0939 1.0000
8.750 1.0644 0.04980 0.04058 -0.0227 0.0891 1.0000
9.000 1.0814 0.05346 0.04424 -0.0218 0.0850 1.0000
9.250 1.0884 0.05814 0.04935 -0.0202 0.0845 1.0000
9.500 1.0913 0.06292 0.05457 -0.0185 0.0846 1.0000
9.750 1.0764 0.06745 0.05987 -0.0160 0.0862 1.0000
10.000 1.0481 0.07313 0.06610 -0.0143 0.0885 1.0000
10.250 1.0200 0.07844 0.07168 -0.0135 0.0903 1.0000
10.500 0.9911 0.08415 0.07754 -0.0144 0.0921 1.0000
10.750 0.9654 0.09081 0.08428 -0.0174 0.0938 1.0000
11.000 0.9474 0.09790 0.09139 -0.0210 0.0956 1.0000
11.250 0.9427 0.10410 0.09759 -0.0228 0.0970 1.0000
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Polar data table (+)
Polar graphs
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