GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 426 AIRFOIL (goe426-il) Reynolds number: 200,000 Max Cl/Cd: 75.9 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe426-il-200000.txt Download as CSV file: xf-goe426-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 426 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2658 0.10014 0.09676 -0.0450 1.0000 0.0584
-9.250 -0.2739 0.09877 0.09546 -0.0427 1.0000 0.0591
-9.000 -0.2703 0.09612 0.09286 -0.0440 0.9975 0.0606
-8.750 -0.2545 0.09092 0.08766 -0.0527 0.9892 0.0639
-8.500 -0.2544 0.08187 0.07863 -0.0702 0.9755 0.0661
-8.250 -0.2211 0.07998 0.07671 -0.0675 0.9732 0.0675
-8.000 -0.1927 0.07688 0.07360 -0.0709 0.9676 0.0699
-7.750 -0.1713 0.07177 0.06847 -0.0799 0.9568 0.0740
-7.500 -0.1801 0.05966 0.05613 -0.1031 0.9288 0.0780
-7.250 -0.1544 0.05817 0.05471 -0.1014 0.9180 0.0794
-7.000 -0.1374 0.05603 0.05252 -0.1018 0.9030 0.0813
-6.750 -0.1404 0.05192 0.04794 -0.1075 0.8808 0.0888
-6.500 -0.1366 0.04716 0.04298 -0.1086 0.8653 0.0913
-6.250 -0.1179 0.04512 0.04099 -0.1077 0.8519 0.0930
-6.000 -0.1010 0.04329 0.03907 -0.1072 0.8381 0.0959
-5.750 -0.0915 0.04028 0.03549 -0.1086 0.8237 0.1059
-5.500 -0.0712 0.03825 0.03353 -0.1079 0.8112 0.1086
-5.250 -0.0515 0.03677 0.03188 -0.1076 0.7976 0.1152
-5.000 -0.0344 0.03426 0.02908 -0.1078 0.7849 0.1235
-4.750 -0.0126 0.03280 0.02751 -0.1075 0.7730 0.1296
-4.500 0.0076 0.03090 0.02532 -0.1074 0.7618 0.1408
-4.250 0.0387 0.02394 0.01682 -0.1062 0.7516 0.0742
-4.000 0.0638 0.02215 0.01471 -0.1057 0.7413 0.0718
-3.750 0.0902 0.02039 0.01243 -0.1049 0.7311 0.0679
-3.500 0.1173 0.01965 0.01140 -0.1043 0.7206 0.0662
-3.250 0.1445 0.01895 0.01048 -0.1039 0.7119 0.0658
-3.000 0.1707 0.01809 0.00952 -0.1035 0.7017 0.0659
-2.750 0.1976 0.01725 0.00855 -0.1031 0.6941 0.0663
-2.500 0.2234 0.01650 0.00781 -0.1027 0.6849 0.0676
-2.250 0.2501 0.01606 0.00731 -0.1024 0.6780 0.0701
-2.000 0.2761 0.01565 0.00692 -0.1020 0.6695 0.0722
-1.750 0.3029 0.01528 0.00647 -0.1017 0.6630 0.0740
-1.500 0.3292 0.01499 0.00616 -0.1013 0.6557 0.0761
-1.250 0.3556 0.01459 0.00576 -0.1010 0.6490 0.0800
-1.000 0.3827 0.01443 0.00555 -0.1009 0.6431 0.0868
-0.750 0.4094 0.01420 0.00535 -0.1006 0.6362 0.0998
-0.500 0.4315 0.01280 0.00514 -0.1003 0.6308 0.4350
-0.250 0.4509 0.01227 0.00540 -0.0983 0.6252 0.6697
0.000 0.4720 0.01211 0.00551 -0.0963 0.6192 0.7674
0.250 0.4943 0.01194 0.00548 -0.0944 0.6143 0.8477
0.500 0.5401 0.01182 0.00545 -0.0974 0.6081 0.9569
0.750 0.5798 0.01191 0.00540 -0.1001 0.6019 1.0000
1.000 0.6070 0.01207 0.00539 -0.1001 0.5973 1.0000
1.250 0.6329 0.01225 0.00551 -0.0998 0.5916 1.0000
1.500 0.6596 0.01241 0.00558 -0.0997 0.5861 1.0000
1.750 0.6874 0.01259 0.00562 -0.0997 0.5816 1.0000
2.000 0.7135 0.01280 0.00579 -0.0995 0.5761 1.0000
2.250 0.7402 0.01298 0.00591 -0.0993 0.5706 1.0000
2.500 0.7680 0.01318 0.00600 -0.0993 0.5661 1.0000
2.750 0.7944 0.01341 0.00621 -0.0992 0.5610 1.0000
3.000 0.8206 0.01361 0.00640 -0.0989 0.5552 1.0000
3.250 0.8482 0.01382 0.00652 -0.0989 0.5504 1.0000
3.500 0.8750 0.01409 0.00676 -0.0988 0.5457 1.0000
3.750 0.9006 0.01432 0.00702 -0.0985 0.5399 1.0000
4.000 0.9280 0.01453 0.00717 -0.0984 0.5349 1.0000
4.250 0.9551 0.01482 0.00741 -0.0984 0.5300 1.0000
4.500 0.9799 0.01506 0.00774 -0.0979 0.5242 1.0000
4.750 1.0069 0.01530 0.00794 -0.0978 0.5192 1.0000
5.000 1.0348 0.01561 0.00818 -0.0979 0.5146 1.0000
5.250 1.0583 0.01587 0.00855 -0.0973 0.5083 1.0000
5.500 1.0849 0.01610 0.00878 -0.0971 0.5030 1.0000
5.750 1.1133 0.01643 0.00904 -0.0973 0.4987 1.0000
6.000 1.1357 0.01672 0.00949 -0.0965 0.4925 1.0000
6.250 1.1618 0.01696 0.00975 -0.0963 0.4870 1.0000
6.500 1.1903 0.01727 0.00998 -0.0965 0.4826 1.0000
6.750 1.2117 0.01760 0.01049 -0.0955 0.4763 1.0000
7.000 1.2374 0.01786 0.01079 -0.0952 0.4710 1.0000
7.250 1.2656 0.01813 0.01100 -0.0953 0.4662 1.0000
7.500 1.2857 0.01841 0.01147 -0.0942 0.4591 1.0000
7.750 1.3119 0.01856 0.01162 -0.0939 0.4533 1.0000
8.000 1.3349 0.01882 0.01198 -0.0932 0.4468 1.0000
8.250 1.3575 0.01892 0.01213 -0.0923 0.4392 1.0000
8.500 1.3800 0.01902 0.01227 -0.0914 0.4314 1.0000
8.750 1.4010 0.01897 0.01226 -0.0902 0.4217 1.0000
9.000 1.4183 0.01900 0.01239 -0.0884 0.4105 1.0000
9.250 1.4353 0.01902 0.01243 -0.0866 0.3985 1.0000
9.500 1.4512 0.01912 0.01254 -0.0846 0.3860 1.0000
9.750 1.4663 0.01935 0.01281 -0.0826 0.3742 1.0000
10.000 1.4797 0.01969 0.01326 -0.0804 0.3624 1.0000
10.250 1.4917 0.02009 0.01371 -0.0779 0.3505 1.0000
10.500 1.4994 0.02055 0.01421 -0.0748 0.3381 1.0000
10.750 1.5051 0.02114 0.01483 -0.0715 0.3247 1.0000
11.000 1.5085 0.02190 0.01561 -0.0682 0.3092 1.0000
11.250 1.5086 0.02290 0.01662 -0.0648 0.2897 1.0000
11.500 1.5041 0.02428 0.01795 -0.0612 0.2669 1.0000
11.750 1.4942 0.02622 0.01979 -0.0576 0.2354 1.0000
12.000 1.4752 0.02911 0.02248 -0.0541 0.1967 1.0000
12.250 1.4510 0.03291 0.02605 -0.0512 0.1592 1.0000
12.500 1.4272 0.03718 0.03015 -0.0491 0.1309 1.0000
12.750 1.4042 0.04177 0.03462 -0.0477 0.1071 1.0000
13.000 1.3822 0.04660 0.03934 -0.0468 0.0847 1.0000
13.250 1.3623 0.05153 0.04417 -0.0465 0.0688 1.0000
13.500 1.3455 0.05638 0.04898 -0.0464 0.0595 1.0000
13.750 1.3327 0.06096 0.05361 -0.0466 0.0536 1.0000
14.000 1.3208 0.06558 0.05824 -0.0469 0.0502 1.0000
14.250 1.3126 0.06985 0.06260 -0.0473 0.0473 1.0000
14.500 1.3074 0.07381 0.06664 -0.0478 0.0447 1.0000
14.750 1.3012 0.07795 0.07083 -0.0484 0.0429 1.0000
15.000 1.2943 0.08216 0.07506 -0.0489 0.0413 1.0000
15.250 1.2953 0.08542 0.07842 -0.0494 0.0394 1.0000
15.500 1.2956 0.08878 0.08184 -0.0499 0.0378 1.0000
15.750 1.2964 0.09199 0.08507 -0.0503 0.0365 1.0000
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