GOE 626 AIRFOIL (goe626-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 626 AIRFOIL (goe626-il) Reynolds number: 200,000 Max Cl/Cd: 64.9 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe626-il-200000-n5.txt Download as CSV file: xf-goe626-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 626 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6012 0.10868 0.10372 -0.0632 1.0000 0.0365
-16.000 -0.6320 0.09976 0.09460 -0.0680 1.0000 0.0366
-15.750 -0.6469 0.09407 0.08878 -0.0708 1.0000 0.0367
-15.500 -0.6577 0.08929 0.08388 -0.0729 1.0000 0.0368
-15.250 -0.6656 0.08513 0.07963 -0.0747 1.0000 0.0370
-15.000 -0.6726 0.08128 0.07569 -0.0762 1.0000 0.0372
-14.750 -0.6765 0.07807 0.07240 -0.0772 1.0000 0.0374
-14.500 -0.6810 0.07491 0.06916 -0.0780 1.0000 0.0376
-14.250 -0.6772 0.07327 0.06755 -0.0775 1.0000 0.0379
-14.000 -0.6725 0.07186 0.06617 -0.0768 1.0000 0.0383
-13.750 -0.6702 0.07018 0.06451 -0.0762 1.0000 0.0385
-13.500 -0.6690 0.06855 0.06290 -0.0755 1.0000 0.0388
-13.250 -0.6694 0.06684 0.06119 -0.0747 1.0000 0.0390
-13.000 -0.6719 0.06508 0.05944 -0.0737 1.0000 0.0392
-12.750 -0.6758 0.06343 0.05780 -0.0725 1.0000 0.0394
-12.500 -0.6821 0.06178 0.05616 -0.0710 1.0000 0.0396
-12.250 -0.6694 0.05966 0.05402 -0.0732 0.9977 0.0399
-12.000 -0.6524 0.05733 0.05166 -0.0766 0.9939 0.0403
-11.750 -0.6382 0.05506 0.04936 -0.0795 0.9897 0.0408
-11.500 -0.6247 0.05273 0.04699 -0.0825 0.9848 0.0412
-11.250 -0.6082 0.05032 0.04454 -0.0863 0.9807 0.0416
-11.000 -0.6007 0.04785 0.04202 -0.0888 0.9727 0.0421
-10.750 -0.5869 0.04511 0.03922 -0.0931 0.9673 0.0425
-10.500 -0.5854 0.04201 0.03612 -0.0962 0.9568 0.0430
-10.250 -0.5731 0.03825 0.03231 -0.1022 0.9493 0.0436
-10.000 -0.5574 0.03425 0.02820 -0.1088 0.9414 0.0443
-9.750 -0.5283 0.03017 0.02397 -0.1171 0.9378 0.0452
-9.500 -0.5107 0.02701 0.02064 -0.1210 0.9293 0.0461
-9.250 -0.4808 0.02496 0.01844 -0.1247 0.9253 0.0473
-9.000 -0.4477 0.02326 0.01663 -0.1283 0.9225 0.0489
-8.750 -0.4181 0.02192 0.01522 -0.1306 0.9186 0.0515
-8.500 -0.3949 0.02088 0.01413 -0.1311 0.9117 0.0552
-8.250 -0.3630 0.01980 0.01304 -0.1330 0.9077 0.0645
-8.000 -0.3282 0.01886 0.01205 -0.1352 0.9046 0.0779
-7.750 -0.3023 0.01810 0.01126 -0.1355 0.8982 0.0892
-7.500 -0.2736 0.01731 0.01045 -0.1363 0.8919 0.1026
-7.250 -0.2395 0.01648 0.00963 -0.1381 0.8874 0.1194
-7.000 -0.2105 0.01585 0.00903 -0.1387 0.8804 0.1387
-6.750 -0.1809 0.01539 0.00857 -0.1391 0.8723 0.1551
-6.500 -0.1436 0.01499 0.00819 -0.1408 0.8665 0.1735
-6.250 -0.1187 0.01485 0.00807 -0.1401 0.8558 0.1882
-6.000 -0.0835 0.01470 0.00787 -0.1412 0.8486 0.2006
-5.750 -0.0565 0.01461 0.00770 -0.1408 0.8381 0.2110
-5.500 -0.0227 0.01456 0.00757 -0.1415 0.8294 0.2211
-5.250 0.0044 0.01457 0.00753 -0.1411 0.8177 0.2282
-5.000 0.0355 0.01454 0.00738 -0.1413 0.8067 0.2345
-4.750 0.0644 0.01443 0.00712 -0.1412 0.7938 0.2401
-4.500 0.0926 0.01449 0.00716 -0.1408 0.7796 0.2441
-4.250 0.1213 0.01454 0.00710 -0.1406 0.7643 0.2494
-4.000 0.1499 0.01454 0.00692 -0.1404 0.7475 0.2557
-3.750 0.1779 0.01472 0.00709 -0.1400 0.7289 0.2601
-3.500 0.2057 0.01485 0.00711 -0.1396 0.7096 0.2652
-3.250 0.2333 0.01489 0.00692 -0.1392 0.6909 0.2702
-3.000 0.2602 0.01491 0.00682 -0.1387 0.6739 0.2733
-2.750 0.2869 0.01499 0.00681 -0.1381 0.6588 0.2760
-2.500 0.3136 0.01504 0.00675 -0.1376 0.6455 0.2786
-2.250 0.3403 0.01507 0.00668 -0.1372 0.6337 0.2815
-2.000 0.3670 0.01509 0.00654 -0.1367 0.6227 0.2842
-1.750 0.3938 0.01507 0.00640 -0.1363 0.6121 0.2866
-1.500 0.4208 0.01510 0.00626 -0.1360 0.6029 0.2885
-1.250 0.4472 0.01504 0.00619 -0.1355 0.5936 0.2904
-1.000 0.4738 0.01507 0.00617 -0.1351 0.5849 0.2923
-0.750 0.5002 0.01506 0.00615 -0.1346 0.5756 0.2941
-0.500 0.5265 0.01509 0.00611 -0.1341 0.5666 0.2959
-0.250 0.5529 0.01510 0.00609 -0.1336 0.5580 0.2979
0.000 0.5791 0.01513 0.00607 -0.1331 0.5494 0.3003
0.250 0.6054 0.01517 0.00605 -0.1326 0.5414 0.3027
0.500 0.6314 0.01520 0.00602 -0.1321 0.5323 0.3047
0.750 0.6571 0.01526 0.00599 -0.1315 0.5235 0.3063
1.000 0.6824 0.01525 0.00598 -0.1308 0.5133 0.3080
1.250 0.7074 0.01528 0.00599 -0.1301 0.5040 0.3097
1.500 0.7324 0.01533 0.00604 -0.1294 0.4942 0.3117
1.750 0.7572 0.01542 0.00609 -0.1286 0.4853 0.3140
2.000 0.7821 0.01550 0.00616 -0.1279 0.4762 0.3164
2.250 0.8068 0.01560 0.00622 -0.1272 0.4684 0.3186
2.500 0.8318 0.01569 0.00631 -0.1265 0.4602 0.3207
2.750 0.8560 0.01583 0.00638 -0.1256 0.4527 0.3228
3.000 0.8809 0.01594 0.00648 -0.1249 0.4451 0.3248
3.250 0.9052 0.01605 0.00660 -0.1241 0.4382 0.3269
3.500 0.9292 0.01618 0.00674 -0.1233 0.4316 0.3291
3.750 0.9534 0.01630 0.00690 -0.1225 0.4243 0.3319
4.000 0.9767 0.01648 0.00706 -0.1215 0.4176 0.3348
4.250 1.0008 0.01664 0.00724 -0.1207 0.4116 0.3380
4.500 1.0246 0.01680 0.00743 -0.1199 0.4053 0.3409
4.750 1.0475 0.01700 0.00761 -0.1189 0.3993 0.3437
5.000 1.0705 0.01716 0.00782 -0.1179 0.3928 0.3466
5.250 1.0919 0.01733 0.00803 -0.1167 0.3843 0.3497
5.500 1.1126 0.01755 0.00826 -0.1153 0.3763 0.3531
5.750 1.1336 0.01773 0.00850 -0.1140 0.3681 0.3570
6.000 1.1527 0.01798 0.00872 -0.1123 0.3612 0.3610
6.250 1.1735 0.01816 0.00899 -0.1110 0.3545 0.3656
6.500 1.1923 0.01838 0.00927 -0.1093 0.3474 0.3708
6.750 1.2103 0.01865 0.00957 -0.1076 0.3403 0.3771
7.250 1.2450 0.01925 0.01025 -0.1039 0.3228 0.3911
7.500 1.2628 0.01955 0.01063 -0.1022 0.3137 0.4004
7.750 1.2788 0.01992 0.01104 -0.1003 0.3061 0.4116
8.000 1.2967 0.02025 0.01148 -0.0987 0.2973 0.4277
8.250 1.3121 0.02068 0.01196 -0.0968 0.2887 0.4502
8.500 1.3288 0.02107 0.01248 -0.0951 0.2785 0.4874
8.750 1.3436 0.02149 0.01308 -0.0933 0.2671 0.5603
9.250 1.3678 0.02228 0.01438 -0.0890 0.2399 1.0000
9.750 1.3861 0.02408 0.01607 -0.0844 0.2125 1.0000
10.000 1.3943 0.02511 0.01706 -0.0822 0.2010 1.0000
10.250 1.4014 0.02623 0.01815 -0.0800 0.1917 1.0000
10.500 1.4080 0.02745 0.01933 -0.0778 0.1836 1.0000
10.750 1.4149 0.02870 0.02058 -0.0758 0.1772 1.0000
11.000 1.4219 0.03000 0.02189 -0.0740 0.1714 1.0000
11.250 1.4267 0.03150 0.02340 -0.0721 0.1665 1.0000
11.500 1.4346 0.03284 0.02479 -0.0706 0.1622 1.0000
11.750 1.4413 0.03433 0.02632 -0.0691 0.1575 1.0000
12.000 1.4443 0.03616 0.02816 -0.0675 0.1529 1.0000
12.250 1.4495 0.03788 0.02995 -0.0663 0.1489 1.0000
12.500 1.4568 0.03951 0.03165 -0.0652 0.1444 1.0000
12.750 1.4597 0.04158 0.03377 -0.0641 0.1394 1.0000
13.000 1.4622 0.04378 0.03602 -0.0632 0.1351 1.0000
13.250 1.4687 0.04568 0.03801 -0.0625 0.1291 1.0000
13.500 1.4693 0.04826 0.04063 -0.0619 0.1232 1.0000
13.750 1.4730 0.05060 0.04305 -0.0614 0.1152 1.0000
14.000 1.4720 0.05353 0.04601 -0.0611 0.1059 1.0000
14.250 1.4673 0.05698 0.04946 -0.0610 0.0959 1.0000
14.500 1.4612 0.06071 0.05318 -0.0611 0.0889 1.0000
14.750 1.4552 0.06452 0.05701 -0.0613 0.0841 1.0000
15.000 1.4495 0.06840 0.06093 -0.0617 0.0810 1.0000
15.250 1.4448 0.07225 0.06484 -0.0621 0.0787 1.0000
15.500 1.4415 0.07598 0.06865 -0.0627 0.0771 1.0000
15.750 1.4375 0.07988 0.07263 -0.0634 0.0756 1.0000
16.000 1.4330 0.08394 0.07676 -0.0642 0.0743 1.0000
16.250 1.4280 0.08815 0.08105 -0.0652 0.0731 1.0000
16.500 1.4230 0.09242 0.08539 -0.0663 0.0721 1.0000
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Polar data table (+)
Polar graphs
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