GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 200,000 Max Cl/Cd: 65.54 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe286-il-200000-n5.txt Download as CSV file: xf-goe286-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3983 0.10578 0.10233 -0.0152 1.0000 0.0303
-9.000 -0.3961 0.10184 0.09842 -0.0186 1.0000 0.0304
-8.750 -0.3932 0.09788 0.09449 -0.0216 1.0000 0.0305
-8.500 -0.3904 0.09393 0.09057 -0.0242 1.0000 0.0305
-8.250 -0.3856 0.08997 0.08665 -0.0239 1.0000 0.0309
-8.000 -0.3757 0.08744 0.08413 -0.0228 1.0000 0.0315
-7.750 -0.3697 0.08467 0.08139 -0.0235 1.0000 0.0321
-7.500 -0.3631 0.08159 0.07834 -0.0256 1.0000 0.0329
-7.250 -0.3564 0.07860 0.07538 -0.0278 1.0000 0.0345
-7.000 -0.3492 0.07245 0.06917 -0.0405 0.9983 0.0381
-6.750 -0.3212 0.06605 0.06262 -0.0490 0.9903 0.0382
-6.500 -0.2942 0.06023 0.05665 -0.0552 0.9832 0.0383
-6.250 -0.2802 0.05827 0.05481 -0.0534 0.9763 0.0366
-6.000 -0.2522 0.05293 0.04931 -0.0593 0.9664 0.0362
-5.750 -0.2236 0.04757 0.04371 -0.0644 0.9552 0.0361
-5.500 -0.1977 0.04267 0.03857 -0.0677 0.9420 0.0348
-5.250 -0.1728 0.03786 0.03344 -0.0699 0.9265 0.0342
-5.000 -0.1484 0.03413 0.02936 -0.0709 0.9088 0.0353
-4.750 -0.1240 0.03031 0.02512 -0.0713 0.8902 0.0355
-4.500 -0.0996 0.02702 0.02140 -0.0711 0.8717 0.0353
-4.250 -0.0747 0.02433 0.01825 -0.0707 0.8538 0.0354
-4.000 -0.0493 0.02228 0.01575 -0.0702 0.8363 0.0361
-3.750 -0.0236 0.02073 0.01378 -0.0695 0.8178 0.0369
-3.500 0.0024 0.01937 0.01204 -0.0689 0.7980 0.0371
-3.250 0.0289 0.01825 0.01057 -0.0683 0.7759 0.0373
-3.000 0.0556 0.01734 0.00935 -0.0678 0.7507 0.0375
-2.750 0.0824 0.01659 0.00833 -0.0673 0.7222 0.0378
-2.500 0.1091 0.01599 0.00746 -0.0668 0.6930 0.0380
-2.250 0.1357 0.01546 0.00668 -0.0663 0.6686 0.0384
-2.000 0.1623 0.01480 0.00585 -0.0660 0.6483 0.0396
-1.750 0.1894 0.01444 0.00538 -0.0657 0.6312 0.0408
-1.500 0.2167 0.01413 0.00495 -0.0655 0.6162 0.0416
-1.250 0.2443 0.01383 0.00457 -0.0653 0.6030 0.0422
-1.000 0.2720 0.01358 0.00424 -0.0652 0.5906 0.0430
-0.750 0.2998 0.01337 0.00396 -0.0651 0.5776 0.0439
-0.500 0.3278 0.01319 0.00372 -0.0650 0.5637 0.0451
-0.250 0.3558 0.01306 0.00352 -0.0650 0.5482 0.0464
0.000 0.3837 0.01295 0.00334 -0.0649 0.5309 0.0483
0.250 0.4116 0.01286 0.00322 -0.0648 0.5112 0.0527
0.500 0.4393 0.01281 0.00314 -0.0648 0.4890 0.0641
0.750 0.4667 0.01275 0.00306 -0.0647 0.4672 0.0982
1.000 0.4934 0.01240 0.00308 -0.0648 0.4476 0.2499
1.250 0.5211 0.01071 0.00312 -0.0646 0.4308 1.0000
1.500 0.5482 0.01092 0.00315 -0.0644 0.4157 1.0000
1.750 0.5753 0.01114 0.00321 -0.0642 0.4015 1.0000
2.000 0.6025 0.01135 0.00329 -0.0641 0.3901 1.0000
2.250 0.6298 0.01153 0.00337 -0.0640 0.3798 1.0000
2.500 0.6570 0.01174 0.00348 -0.0639 0.3701 1.0000
2.750 0.6840 0.01196 0.00361 -0.0637 0.3593 1.0000
3.000 0.7111 0.01217 0.00373 -0.0636 0.3473 1.0000
3.250 0.7380 0.01240 0.00387 -0.0635 0.3340 1.0000
3.500 0.7647 0.01264 0.00403 -0.0634 0.3200 1.0000
3.750 0.7914 0.01289 0.00420 -0.0632 0.3070 1.0000
4.000 0.8180 0.01314 0.00438 -0.0631 0.2967 1.0000
4.250 0.8449 0.01335 0.00458 -0.0630 0.2872 1.0000
4.500 0.8714 0.01361 0.00479 -0.0628 0.2751 1.0000
4.750 0.8978 0.01388 0.00501 -0.0626 0.2638 1.0000
5.000 0.9239 0.01417 0.00527 -0.0625 0.2503 1.0000
5.250 0.9497 0.01449 0.00553 -0.0623 0.2336 1.0000
5.500 0.9750 0.01489 0.00583 -0.0620 0.2104 1.0000
5.750 0.9963 0.01581 0.00638 -0.0614 0.1491 1.0000
6.000 1.0204 0.01635 0.00685 -0.0611 0.1385 1.0000
6.250 1.0453 0.01675 0.00726 -0.0607 0.1346 1.0000
6.500 1.0701 0.01714 0.00768 -0.0604 0.1317 1.0000
6.750 1.0947 0.01754 0.00813 -0.0601 0.1291 1.0000
7.000 1.1191 0.01796 0.00859 -0.0597 0.1268 1.0000
7.250 1.1426 0.01844 0.00912 -0.0592 0.1236 1.0000
7.500 1.1667 0.01884 0.00959 -0.0588 0.1219 1.0000
7.750 1.1906 0.01924 0.01010 -0.0583 0.1201 1.0000
8.000 1.2136 0.01971 0.01066 -0.0578 0.1169 1.0000
8.250 1.2350 0.02033 0.01132 -0.0571 0.1123 1.0000
8.500 1.2557 0.02098 0.01202 -0.0563 0.1078 1.0000
8.750 1.2789 0.02137 0.01255 -0.0558 0.1037 1.0000
9.000 1.3001 0.02192 0.01317 -0.0550 0.0979 1.0000
9.250 1.3226 0.02233 0.01369 -0.0544 0.0901 1.0000
9.500 1.3415 0.02303 0.01432 -0.0535 0.0657 1.0000
9.750 1.3562 0.02407 0.01526 -0.0521 0.0590 1.0000
10.000 1.3699 0.02510 0.01636 -0.0505 0.0550 1.0000
10.250 1.3804 0.02630 0.01764 -0.0486 0.0514 1.0000
10.500 1.3932 0.02719 0.01866 -0.0469 0.0484 1.0000
10.750 1.4019 0.02825 0.01985 -0.0446 0.0441 1.0000
11.000 1.4113 0.02935 0.02108 -0.0427 0.0398 1.0000
11.250 1.4228 0.03034 0.02220 -0.0412 0.0317 1.0000
11.500 1.4262 0.03204 0.02381 -0.0393 0.0218 1.0000
11.750 1.4279 0.03400 0.02577 -0.0376 0.0191 1.0000
12.000 1.4301 0.03608 0.02796 -0.0363 0.0180 1.0000
12.250 1.4308 0.03846 0.03048 -0.0353 0.0171 1.0000
12.500 1.4296 0.04119 0.03335 -0.0346 0.0164 1.0000
12.750 1.4263 0.04435 0.03666 -0.0344 0.0158 1.0000
13.000 1.4207 0.04801 0.04048 -0.0346 0.0153 1.0000
13.250 1.4139 0.05205 0.04468 -0.0353 0.0149 1.0000
13.500 1.4089 0.05596 0.04876 -0.0360 0.0146 1.0000
13.750 1.4020 0.06019 0.05316 -0.0370 0.0142 1.0000
14.000 1.3935 0.06471 0.05785 -0.0381 0.0140 1.0000
14.250 1.3837 0.06951 0.06280 -0.0393 0.0137 1.0000
14.500 1.3733 0.07452 0.06797 -0.0408 0.0134 1.0000
14.750 1.3626 0.07974 0.07333 -0.0424 0.0132 1.0000
15.000 1.3518 0.08510 0.07882 -0.0442 0.0130 1.0000
15.250 1.3411 0.09053 0.08439 -0.0461 0.0129 1.0000
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Polar data table (+)
Polar graphs
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