GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 481A AIRFOIL (goe481a-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.31 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe481a-il-1000000-n5.txt Download as CSV file: xf-goe481a-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 481A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8553 0.03100 0.02743 -0.1625 0.9622 0.0382
-14.750 -0.8515 0.02914 0.02545 -0.1622 0.9604 0.0385
-14.500 -0.8456 0.02755 0.02375 -0.1613 0.9590 0.0385
-14.250 -0.8624 0.02664 0.02275 -0.1546 0.9521 0.0386
-14.000 -0.8497 0.02554 0.02157 -0.1533 0.9496 0.0388
-13.750 -0.8327 0.02450 0.02043 -0.1526 0.9481 0.0389
-13.500 -0.8136 0.02349 0.01934 -0.1522 0.9471 0.0391
-13.250 -0.7921 0.02261 0.01838 -0.1519 0.9463 0.0393
-13.000 -0.7699 0.02174 0.01743 -0.1518 0.9456 0.0395
-12.750 -0.7745 0.02129 0.01691 -0.1458 0.9384 0.0396
-12.500 -0.7548 0.02056 0.01611 -0.1448 0.9365 0.0397
-12.250 -0.7328 0.01990 0.01538 -0.1442 0.9353 0.0398
-12.000 -0.7096 0.01924 0.01465 -0.1437 0.9343 0.0400
-11.750 -0.6842 0.01863 0.01397 -0.1436 0.9333 0.0401
-11.500 -0.6567 0.01800 0.01327 -0.1438 0.9323 0.0402
-11.250 -0.6500 0.01759 0.01281 -0.1397 0.9257 0.0403
-11.000 -0.6299 0.01688 0.01204 -0.1384 0.9225 0.0406
-10.750 -0.6056 0.01627 0.01139 -0.1379 0.9205 0.0409
-10.500 -0.5778 0.01573 0.01080 -0.1380 0.9191 0.0411
-10.250 -0.5474 0.01521 0.01025 -0.1386 0.9178 0.0414
-10.000 -0.5257 0.01484 0.00984 -0.1374 0.9144 0.0416
-9.750 -0.5085 0.01457 0.00954 -0.1351 0.9086 0.0419
-9.500 -0.4784 0.01413 0.00906 -0.1355 0.9056 0.0422
-9.250 -0.4456 0.01369 0.00858 -0.1365 0.9034 0.0424
-9.000 -0.4124 0.01331 0.00815 -0.1376 0.9018 0.0427
-8.750 -0.3926 0.01306 0.00787 -0.1358 0.8976 0.0430
-8.500 -0.3709 0.01277 0.00754 -0.1345 0.8932 0.0432
-8.250 -0.3415 0.01245 0.00718 -0.1347 0.8896 0.0435
-8.000 -0.3081 0.01211 0.00679 -0.1358 0.8867 0.0438
-7.750 -0.2731 0.01178 0.00642 -0.1372 0.8841 0.0441
-7.500 -0.2583 0.01161 0.00622 -0.1342 0.8776 0.0443
-7.250 -0.2298 0.01136 0.00592 -0.1342 0.8720 0.0446
-7.000 -0.1932 0.01108 0.00558 -0.1359 0.8675 0.0448
-6.750 -0.1734 0.01090 0.00538 -0.1340 0.8601 0.0450
-6.500 -0.1449 0.01059 0.00502 -0.1340 0.8519 0.0454
-6.250 -0.1191 0.01037 0.00476 -0.1334 0.8433 0.0458
-6.000 -0.0911 0.01017 0.00450 -0.1332 0.8310 0.0463
-5.750 -0.0682 0.01004 0.00431 -0.1319 0.8143 0.0466
-5.500 -0.0474 0.00998 0.00414 -0.1302 0.7924 0.0471
-5.250 -0.0351 0.01002 0.00403 -0.1266 0.7586 0.0474
-5.000 -0.0271 0.01015 0.00398 -0.1221 0.7215 0.0478
-4.750 -0.0183 0.01029 0.00395 -0.1178 0.6852 0.0482
-4.500 -0.0063 0.01040 0.00390 -0.1142 0.6549 0.0484
-4.250 0.0091 0.01046 0.00384 -0.1114 0.6301 0.0489
-4.000 0.0268 0.01049 0.00378 -0.1090 0.6112 0.0492
-3.750 0.0461 0.01049 0.00370 -0.1070 0.5978 0.0495
-3.500 0.0670 0.01047 0.00364 -0.1053 0.5862 0.0499
-3.250 0.0867 0.01047 0.00357 -0.1034 0.5746 0.0502
-3.000 0.1068 0.01042 0.00348 -0.1015 0.5632 0.0509
-2.750 0.1278 0.01039 0.00341 -0.0999 0.5539 0.0517
-2.500 0.1498 0.01036 0.00335 -0.0984 0.5455 0.0522
-2.250 0.1710 0.01035 0.00330 -0.0968 0.5374 0.0528
-2.000 0.1938 0.01031 0.00325 -0.0955 0.5300 0.0535
-1.750 0.2151 0.01033 0.00321 -0.0939 0.5205 0.0542
-1.500 0.2380 0.01032 0.00318 -0.0927 0.5149 0.0550
-1.250 0.2609 0.01031 0.00315 -0.0914 0.5079 0.0556
-1.000 0.2827 0.01030 0.00312 -0.0899 0.5011 0.0567
-0.750 0.3051 0.01029 0.00309 -0.0886 0.4955 0.0578
-0.500 0.3275 0.01028 0.00308 -0.0872 0.4880 0.0590
-0.250 0.3480 0.01033 0.00308 -0.0855 0.4794 0.0604
0.000 0.3702 0.01035 0.00308 -0.0841 0.4716 0.0615
0.250 0.3919 0.01037 0.00309 -0.0826 0.4643 0.0636
0.500 0.4129 0.01041 0.00311 -0.0810 0.4548 0.0663
0.750 0.4353 0.01042 0.00312 -0.0797 0.4480 0.0698
1.000 0.4566 0.01045 0.00315 -0.0782 0.4410 0.0771
1.250 0.4786 0.01046 0.00319 -0.0768 0.4346 0.0874
1.500 0.5009 0.01048 0.00326 -0.0756 0.4281 0.1036
1.750 0.5220 0.01058 0.00335 -0.0740 0.4191 0.1123
2.000 0.5446 0.01066 0.00342 -0.0728 0.4108 0.1176
2.250 0.5656 0.01077 0.00351 -0.0713 0.4024 0.1218
2.500 0.5871 0.01088 0.00360 -0.0699 0.3935 0.1254
2.750 0.6080 0.01101 0.00370 -0.0684 0.3845 0.1280
3.000 0.6295 0.01113 0.00379 -0.0670 0.3762 0.1306
3.250 0.6509 0.01125 0.00390 -0.0656 0.3681 0.1334
3.500 0.6723 0.01138 0.00401 -0.0642 0.3614 0.1363
3.750 0.6945 0.01150 0.00412 -0.0630 0.3549 0.1392
4.000 0.7161 0.01164 0.00423 -0.0617 0.3487 0.1409
4.250 0.7373 0.01177 0.00436 -0.0603 0.3427 0.1439
4.500 0.7588 0.01189 0.00448 -0.0590 0.3369 0.1458
4.750 0.7795 0.01204 0.00462 -0.0575 0.3308 0.1481
5.000 0.8000 0.01222 0.00478 -0.0561 0.3238 0.1508
5.250 0.8215 0.01237 0.00492 -0.0548 0.3174 0.1530
5.500 0.8422 0.01255 0.00508 -0.0534 0.3114 0.1542
5.750 0.8635 0.01271 0.00524 -0.0522 0.3069 0.1574
6.000 0.8850 0.01287 0.00540 -0.0510 0.3007 0.1599
6.250 0.9052 0.01307 0.00560 -0.0496 0.2946 0.1625
6.500 0.9250 0.01330 0.00581 -0.0481 0.2881 0.1651
6.750 0.9454 0.01351 0.00601 -0.0468 0.2798 0.1679
7.000 0.9645 0.01379 0.00626 -0.0453 0.2712 0.1725
7.250 0.9861 0.01398 0.00647 -0.0443 0.2656 0.1820
7.500 1.0075 0.01419 0.00677 -0.0433 0.2581 0.2350
8.000 1.2262 0.01508 0.00891 -0.0812 0.1946 1.0000
8.250 1.2421 0.01554 0.00932 -0.0793 0.1852 1.0000
8.500 1.2574 0.01603 0.00976 -0.0773 0.1766 1.0000
8.750 1.2748 0.01645 0.01014 -0.0756 0.1713 1.0000
9.000 1.2912 0.01690 0.01058 -0.0738 0.1664 1.0000
9.250 1.3075 0.01737 0.01103 -0.0720 0.1619 1.0000
9.500 1.3252 0.01778 0.01144 -0.0705 0.1594 1.0000
9.750 1.3424 0.01822 0.01187 -0.0690 0.1566 1.0000
10.000 1.3586 0.01870 0.01235 -0.0673 0.1540 1.0000
10.250 1.3740 0.01923 0.01288 -0.0656 0.1513 1.0000
10.500 1.3900 0.01975 0.01341 -0.0639 0.1485 1.0000
10.750 1.4075 0.02020 0.01388 -0.0626 0.1471 1.0000
11.000 1.4236 0.02072 0.01442 -0.0610 0.1453 1.0000
11.250 1.4397 0.02125 0.01497 -0.0595 0.1437 1.0000
11.500 1.4548 0.02185 0.01558 -0.0579 0.1411 1.0000
11.750 1.4685 0.02253 0.01627 -0.0562 0.1390 1.0000
12.000 1.4813 0.02328 0.01702 -0.0544 0.1357 1.0000
12.250 1.4968 0.02390 0.01767 -0.0530 0.1347 1.0000
12.500 1.5110 0.02459 0.01839 -0.0515 0.1319 1.0000
12.750 1.5241 0.02538 0.01918 -0.0499 0.1283 1.0000
13.000 1.5339 0.02637 0.02016 -0.0481 0.1238 1.0000
13.250 1.5459 0.02726 0.02106 -0.0465 0.1198 1.0000
13.500 1.5538 0.02843 0.02221 -0.0446 0.1129 1.0000
13.750 1.5568 0.02998 0.02370 -0.0424 0.1009 1.0000
14.000 1.5568 0.03182 0.02549 -0.0400 0.0905 1.0000
14.250 1.5589 0.03357 0.02723 -0.0381 0.0847 1.0000
14.500 1.5632 0.03523 0.02891 -0.0364 0.0812 1.0000
14.750 1.5689 0.03684 0.03054 -0.0350 0.0790 1.0000
15.000 1.5717 0.03874 0.03247 -0.0335 0.0765 1.0000
15.250 1.5754 0.04063 0.03441 -0.0323 0.0742 1.0000
15.500 1.5806 0.04244 0.03626 -0.0312 0.0729 1.0000
15.750 1.5854 0.04432 0.03819 -0.0302 0.0719 1.0000
16.000 1.5880 0.04646 0.04038 -0.0293 0.0705 1.0000
16.250 1.5889 0.04881 0.04278 -0.0284 0.0690 1.0000
16.500 1.5895 0.05127 0.04529 -0.0277 0.0677 1.0000
16.750 1.5920 0.05356 0.04764 -0.0271 0.0669 1.0000
17.000 1.5944 0.05589 0.05003 -0.0266 0.0661 1.0000
17.250 1.5954 0.05839 0.05259 -0.0261 0.0649 1.0000
17.500 1.5955 0.06104 0.05531 -0.0257 0.0642 1.0000
17.750 1.5922 0.06411 0.05843 -0.0254 0.0626 1.0000
18.000 1.5890 0.06718 0.06155 -0.0252 0.0614 1.0000
18.250 1.5859 0.07026 0.06469 -0.0251 0.0605 1.0000
18.500 1.5845 0.07322 0.06773 -0.0251 0.0599 1.0000
18.750 1.5830 0.07620 0.07078 -0.0251 0.0593 1.0000
19.000 1.5814 0.07923 0.07387 -0.0252 0.0585 1.0000
19.250 1.5771 0.08258 0.07730 -0.0254 0.0576 1.0000
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