GOE 13K AIRFOIL (goe13k-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 13K AIRFOIL (goe13k-il) Reynolds number: 500,000 Max Cl/Cd: 85.81 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe13k-il-500000-n5.txt Download as CSV file: xf-goe13k-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 13K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.0904 0.10120 0.09801 -0.1553 0.9245 0.0323
-13.000 -0.3944 0.04023 0.03655 -0.1977 0.9166 0.0406
-12.750 -0.4452 0.03459 0.03051 -0.1968 0.9093 0.0409
-12.500 -0.4596 0.03144 0.02697 -0.1951 0.9064 0.0414
-12.250 -0.4548 0.02943 0.02471 -0.1943 0.9045 0.0417
-12.000 -0.4840 0.02920 0.02443 -0.1839 0.8966 0.0418
-11.750 -0.4757 0.02821 0.02335 -0.1816 0.8937 0.0421
-11.500 -0.4588 0.02715 0.02218 -0.1810 0.8918 0.0423
-11.250 -0.4354 0.02634 0.02129 -0.1813 0.8903 0.0426
-11.000 -0.4102 0.02546 0.02030 -0.1821 0.8890 0.0429
-10.750 -0.4301 0.02532 0.02013 -0.1727 0.8826 0.0430
-10.500 -0.4223 0.02473 0.01946 -0.1694 0.8793 0.0433
-10.250 -0.4057 0.02416 0.01879 -0.1679 0.8770 0.0436
-10.000 -0.3859 0.02332 0.01782 -0.1672 0.8752 0.0440
-9.750 -0.3628 0.02241 0.01676 -0.1671 0.8737 0.0444
-9.500 -0.3364 0.02150 0.01570 -0.1677 0.8724 0.0449
-9.250 -0.3564 0.02144 0.01560 -0.1578 0.8662 0.0450
-9.000 -0.3474 0.02082 0.01486 -0.1544 0.8629 0.0453
-8.750 -0.3303 0.02025 0.01417 -0.1526 0.8606 0.0458
-8.500 -0.3085 0.01960 0.01339 -0.1518 0.8589 0.0462
-8.250 -0.2831 0.01895 0.01260 -0.1518 0.8575 0.0466
-8.000 -0.2550 0.01834 0.01186 -0.1523 0.8563 0.0470
-7.750 -0.2494 0.01803 0.01148 -0.1478 0.8530 0.0471
-7.500 -0.2511 0.01792 0.01130 -0.1416 0.8484 0.0473
-7.250 -0.2348 0.01758 0.01087 -0.1394 0.8457 0.0476
-7.000 -0.2133 0.01714 0.01035 -0.1383 0.8436 0.0478
-6.750 -0.1883 0.01639 0.00952 -0.1381 0.8420 0.0483
-6.500 -0.1597 0.01586 0.00894 -0.1385 0.8407 0.0487
-6.250 -0.1291 0.01541 0.00844 -0.1394 0.8396 0.0491
-6.000 -0.1281 0.01536 0.00837 -0.1338 0.8357 0.0493
-5.750 -0.1210 0.01527 0.00827 -0.1294 0.8320 0.0496
-5.500 -0.1027 0.01509 0.00807 -0.1274 0.8295 0.0502
-5.250 -0.0802 0.01484 0.00779 -0.1264 0.8275 0.0506
-5.000 -0.0544 0.01451 0.00741 -0.1261 0.8259 0.0510
-4.750 -0.0256 0.01419 0.00704 -0.1265 0.8247 0.0514
-4.500 0.0049 0.01388 0.00669 -0.1272 0.8235 0.0519
-4.250 0.0201 0.01374 0.00653 -0.1246 0.8210 0.0523
-4.000 0.0177 0.01381 0.00659 -0.1180 0.8162 0.0527
-3.750 0.0354 0.01366 0.00641 -0.1159 0.8134 0.0530
-3.500 0.0588 0.01341 0.00614 -0.1150 0.8109 0.0534
-3.250 0.0867 0.01319 0.00587 -0.1151 0.8093 0.0539
-3.000 0.1192 0.01292 0.00557 -0.1162 0.8077 0.0544
-2.750 0.1315 0.01286 0.00550 -0.1129 0.8044 0.0546
-2.500 0.1357 0.01293 0.00556 -0.1078 0.7997 0.0549
-2.250 0.1529 0.01274 0.00537 -0.1055 0.7969 0.0558
-2.000 0.1763 0.01255 0.00519 -0.1047 0.7950 0.0567
-1.750 0.2048 0.01236 0.00499 -0.1049 0.7934 0.0574
-1.500 0.2362 0.01215 0.00478 -0.1057 0.7919 0.0585
-1.250 0.2518 0.01214 0.00477 -0.1031 0.7892 0.0592
-1.000 0.2561 0.01227 0.00492 -0.0981 0.7847 0.0598
-0.750 0.2746 0.01224 0.00488 -0.0961 0.7818 0.0607
-0.500 0.2988 0.01215 0.00479 -0.0954 0.7795 0.0616
-0.250 0.3281 0.01201 0.00464 -0.0958 0.7776 0.0626
0.000 0.3591 0.01187 0.00450 -0.0965 0.7762 0.0638
0.250 0.3753 0.01190 0.00455 -0.0941 0.7733 0.0655
0.500 0.3823 0.01207 0.00476 -0.0898 0.7693 0.0669
0.750 0.4007 0.01210 0.00481 -0.0879 0.7661 0.0700
1.000 0.4251 0.01207 0.00479 -0.0872 0.7640 0.0731
1.250 0.4553 0.01193 0.00469 -0.0878 0.7618 0.0788
1.500 0.4871 0.01175 0.00464 -0.0888 0.7604 0.1091
1.750 0.5031 0.01183 0.00482 -0.0865 0.7572 0.1351
2.000 0.5129 0.01204 0.00510 -0.0829 0.7529 0.1498
2.250 0.5335 0.01209 0.00522 -0.0815 0.7497 0.1686
2.500 0.5626 0.01196 0.00525 -0.0821 0.7474 0.2124
3.000 0.9215 0.01099 0.00656 -0.1521 0.7493 1.0000
3.250 0.9448 0.01101 0.00655 -0.1513 0.7453 1.0000
3.500 0.9533 0.01125 0.00679 -0.1472 0.7380 1.0000
3.750 0.9685 0.01139 0.00692 -0.1447 0.7309 1.0000
4.000 0.9758 0.01166 0.00716 -0.1404 0.7191 1.0000
4.250 0.9832 0.01194 0.00738 -0.1361 0.7011 1.0000
4.500 0.9883 0.01231 0.00765 -0.1314 0.6776 1.0000
4.750 0.9734 0.01321 0.00827 -0.1227 0.6140 1.0000
5.000 0.9188 0.01564 0.01013 -0.1068 0.5104 1.0000
5.250 0.8968 0.01743 0.01158 -0.0979 0.4545 1.0000
5.500 0.9021 0.01827 0.01231 -0.0941 0.4333 1.0000
5.750 0.9118 0.01897 0.01293 -0.0911 0.4165 1.0000
6.000 0.9254 0.01953 0.01344 -0.0888 0.4058 1.0000
6.250 0.9398 0.02006 0.01394 -0.0867 0.3955 1.0000
6.500 0.9532 0.02065 0.01448 -0.0845 0.3846 1.0000
6.750 0.9703 0.02108 0.01491 -0.0829 0.3748 1.0000
7.000 0.9846 0.02165 0.01544 -0.0808 0.3638 1.0000
7.250 0.9997 0.02220 0.01596 -0.0790 0.3514 1.0000
7.500 1.0147 0.02276 0.01649 -0.0771 0.3387 1.0000
7.750 1.0278 0.02342 0.01708 -0.0750 0.3198 1.0000
8.000 1.0383 0.02423 0.01777 -0.0726 0.2950 1.0000
8.250 1.0466 0.02517 0.01855 -0.0698 0.2639 1.0000
8.750 1.0627 0.02713 0.02013 -0.0644 0.1977 1.0000
9.000 1.0733 0.02800 0.02088 -0.0622 0.1725 1.0000
9.250 1.0857 0.02880 0.02158 -0.0603 0.1540 1.0000
9.500 1.0991 0.02954 0.02225 -0.0585 0.1392 1.0000
9.750 1.1133 0.03024 0.02290 -0.0569 0.1277 1.0000
10.000 1.1270 0.03099 0.02360 -0.0552 0.1176 1.0000
10.250 1.1413 0.03171 0.02430 -0.0536 0.1104 1.0000
10.500 1.1559 0.03242 0.02500 -0.0521 0.1049 1.0000
10.750 1.1705 0.03315 0.02571 -0.0507 0.0988 1.0000
11.000 1.1846 0.03390 0.02646 -0.0492 0.0943 1.0000
11.250 1.1994 0.03462 0.02720 -0.0478 0.0910 1.0000
11.500 1.2125 0.03545 0.02801 -0.0462 0.0857 1.0000
11.750 1.2259 0.03626 0.02883 -0.0447 0.0823 1.0000
12.000 1.2408 0.03700 0.02960 -0.0434 0.0797 1.0000
12.250 1.2539 0.03785 0.03047 -0.0420 0.0762 1.0000
12.500 1.2662 0.03878 0.03141 -0.0405 0.0737 1.0000
12.750 1.2794 0.03965 0.03230 -0.0391 0.0712 1.0000
13.000 1.2928 0.04051 0.03320 -0.0378 0.0691 1.0000
13.250 1.3051 0.04146 0.03417 -0.0364 0.0666 1.0000
13.500 1.3160 0.04252 0.03525 -0.0349 0.0645 1.0000
13.750 1.3279 0.04351 0.03627 -0.0335 0.0625 1.0000
14.000 1.3401 0.04448 0.03730 -0.0322 0.0609 1.0000
14.250 1.3513 0.04555 0.03842 -0.0309 0.0590 1.0000
14.500 1.3612 0.04673 0.03961 -0.0294 0.0566 1.0000
14.750 1.3710 0.04793 0.04085 -0.0280 0.0548 1.0000
15.000 1.3818 0.04907 0.04205 -0.0268 0.0531 1.0000
15.250 1.3919 0.05027 0.04331 -0.0255 0.0511 1.0000
15.500 1.4011 0.05156 0.04463 -0.0242 0.0490 1.0000
15.750 1.4088 0.05298 0.04610 -0.0228 0.0473 1.0000
16.000 1.4179 0.05430 0.04748 -0.0216 0.0450 1.0000
16.250 1.4257 0.05575 0.04896 -0.0204 0.0426 1.0000
16.500 1.4318 0.05737 0.05063 -0.0191 0.0405 1.0000
16.750 1.4389 0.05894 0.05224 -0.0179 0.0377 1.0000
17.250 1.4487 0.06254 0.05594 -0.0156 0.0341 1.0000
17.500 1.4525 0.06447 0.05793 -0.0144 0.0321 1.0000
17.750 1.4545 0.06662 0.06010 -0.0133 0.0297 1.0000
18.000 1.4569 0.06878 0.06233 -0.0123 0.0284 1.0000
18.250 1.4586 0.07105 0.06467 -0.0114 0.0273 1.0000
18.500 1.4580 0.07362 0.06730 -0.0105 0.0260 1.0000
18.750 1.4584 0.07613 0.06990 -0.0097 0.0252 1.0000
19.000 1.4583 0.07873 0.07259 -0.0091 0.0242 1.0000
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