GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 502 AIRFOIL (goe502-il) Reynolds number: 500,000 Max Cl/Cd: 100.36 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe502-il-500000-n5.txt Download as CSV file: xf-goe502-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 502 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5505 0.07311 0.06944 -0.1084 0.9826 0.0327
-14.500 -0.5596 0.06725 0.06348 -0.1136 0.9781 0.0329
-14.250 -0.5645 0.06230 0.05845 -0.1181 0.9729 0.0330
-13.750 -0.5698 0.05332 0.04931 -0.1271 0.9625 0.0333
-13.500 -0.5664 0.04926 0.04517 -0.1319 0.9577 0.0335
-13.250 -0.5602 0.04516 0.04097 -0.1375 0.9534 0.0336
-13.000 -0.5535 0.04139 0.03712 -0.1426 0.9466 0.0338
-12.750 -0.5372 0.03761 0.03323 -0.1494 0.9420 0.0341
-12.500 -0.5171 0.03388 0.02937 -0.1569 0.9368 0.0343
-12.250 -0.4991 0.03043 0.02579 -0.1637 0.9287 0.0347
-12.000 -0.4809 0.02696 0.02214 -0.1709 0.9202 0.0349
-11.750 -0.4651 0.02486 0.01987 -0.1742 0.9115 0.0352
-11.250 -0.4305 0.02248 0.01723 -0.1757 0.8981 0.0358
-11.000 -0.4111 0.02155 0.01618 -0.1758 0.8915 0.0361
-10.750 -0.3903 0.02072 0.01522 -0.1760 0.8851 0.0364
-10.500 -0.3724 0.02001 0.01441 -0.1752 0.8766 0.0367
-10.250 -0.3501 0.01928 0.01358 -0.1752 0.8685 0.0369
-10.000 -0.3313 0.01865 0.01291 -0.1743 0.8592 0.0372
-9.750 -0.3083 0.01808 0.01226 -0.1740 0.8499 0.0375
-9.500 -0.2871 0.01758 0.01171 -0.1733 0.8386 0.0379
-9.250 -0.2640 0.01711 0.01116 -0.1728 0.8274 0.0382
-9.000 -0.2409 0.01666 0.01063 -0.1723 0.8153 0.0386
-8.750 -0.2173 0.01625 0.01013 -0.1718 0.8035 0.0391
-8.500 -0.1935 0.01587 0.00964 -0.1713 0.7912 0.0396
-8.250 -0.1697 0.01551 0.00917 -0.1707 0.7786 0.0402
-8.000 -0.1454 0.01519 0.00873 -0.1702 0.7677 0.0407
-7.750 -0.1209 0.01490 0.00832 -0.1697 0.7586 0.0411
-7.500 -0.0968 0.01448 0.00785 -0.1692 0.7504 0.0416
-7.250 -0.0722 0.01416 0.00746 -0.1687 0.7424 0.0421
-7.000 -0.0468 0.01388 0.00713 -0.1684 0.7355 0.0426
-6.750 -0.0213 0.01362 0.00681 -0.1680 0.7290 0.0432
-6.500 0.0044 0.01338 0.00650 -0.1676 0.7232 0.0439
-6.250 0.0306 0.01314 0.00621 -0.1673 0.7182 0.0446
-6.000 0.0569 0.01292 0.00594 -0.1670 0.7130 0.0453
-5.750 0.0833 0.01274 0.00569 -0.1667 0.7074 0.0460
-5.500 0.1090 0.01246 0.00537 -0.1663 0.7020 0.0469
-5.250 0.1356 0.01224 0.00512 -0.1661 0.6974 0.0478
-5.000 0.1623 0.01203 0.00490 -0.1658 0.6926 0.0487
-4.750 0.1888 0.01186 0.00468 -0.1655 0.6873 0.0496
-4.500 0.2154 0.01173 0.00448 -0.1651 0.6819 0.0506
-4.250 0.2421 0.01157 0.00429 -0.1648 0.6770 0.0515
-4.000 0.2687 0.01135 0.00406 -0.1645 0.6718 0.0528
-3.750 0.2953 0.01120 0.00388 -0.1641 0.6662 0.0543
-3.500 0.3217 0.01110 0.00372 -0.1637 0.6605 0.0558
-3.250 0.3485 0.01097 0.00357 -0.1634 0.6547 0.0574
-3.000 0.3748 0.01083 0.00341 -0.1629 0.6479 0.0595
-2.750 0.4009 0.01074 0.00328 -0.1624 0.6416 0.0622
-2.500 0.4272 0.01058 0.00314 -0.1620 0.6349 0.0680
-2.250 0.4524 0.01031 0.00301 -0.1615 0.6267 0.1076
-2.000 0.4778 0.01021 0.00295 -0.1609 0.6190 0.1273
-1.750 0.5037 0.01014 0.00290 -0.1604 0.6104 0.1410
-1.500 0.5286 0.01012 0.00287 -0.1597 0.6016 0.1534
-1.250 0.5540 0.01009 0.00285 -0.1590 0.5917 0.1667
-0.750 0.6034 0.01009 0.00285 -0.1575 0.5730 0.1939
-0.500 0.6275 0.01014 0.00287 -0.1566 0.5642 0.2052
-0.250 0.6524 0.01017 0.00290 -0.1559 0.5554 0.2166
0.000 0.6761 0.01025 0.00295 -0.1549 0.5473 0.2287
0.250 0.7014 0.01028 0.00300 -0.1543 0.5404 0.2396
0.500 0.7256 0.01036 0.00306 -0.1534 0.5332 0.2502
0.750 0.7498 0.01044 0.00314 -0.1525 0.5268 0.2609
1.000 0.7747 0.01051 0.00320 -0.1518 0.5206 0.2704
1.250 0.7988 0.01058 0.00329 -0.1509 0.5149 0.2798
1.500 0.8224 0.01069 0.00337 -0.1499 0.5095 0.2896
1.750 0.8471 0.01074 0.00346 -0.1492 0.5044 0.3010
2.000 0.8706 0.01082 0.00355 -0.1482 0.4991 0.3113
2.250 0.8930 0.01091 0.00365 -0.1470 0.4942 0.3211
2.500 0.9157 0.01101 0.00375 -0.1459 0.4899 0.3322
2.750 0.9395 0.01106 0.00386 -0.1450 0.4854 0.3435
3.000 0.9624 0.01116 0.00397 -0.1439 0.4804 0.3543
3.250 0.9844 0.01127 0.00411 -0.1427 0.4757 0.3666
3.500 1.0063 0.01141 0.00425 -0.1414 0.4712 0.3793
3.750 1.0294 0.01149 0.00440 -0.1404 0.4660 0.3939
4.000 1.0509 0.01162 0.00456 -0.1391 0.4596 0.4095
4.250 1.0710 0.01181 0.00474 -0.1376 0.4538 0.4253
4.500 1.0938 0.01192 0.00491 -0.1365 0.4488 0.4415
5.000 1.1351 0.01224 0.00530 -0.1337 0.4371 0.4787
5.500 1.1775 0.01251 0.00570 -0.1312 0.4264 0.5228
5.750 1.1961 0.01266 0.00595 -0.1295 0.4200 0.5639
6.250 1.2485 0.01244 0.00653 -0.1292 0.4080 1.0000
6.500 1.2680 0.01271 0.00678 -0.1277 0.4021 1.0000
6.750 1.2871 0.01300 0.00705 -0.1262 0.3963 1.0000
7.000 1.3070 0.01327 0.00731 -0.1248 0.3891 1.0000
7.250 1.3235 0.01366 0.00765 -0.1229 0.3814 1.0000
7.500 1.3429 0.01396 0.00796 -0.1215 0.3743 1.0000
7.750 1.3600 0.01435 0.00832 -0.1198 0.3665 1.0000
8.000 1.3774 0.01474 0.00870 -0.1182 0.3597 1.0000
8.250 1.3928 0.01522 0.00915 -0.1163 0.3494 1.0000
8.500 1.4083 0.01571 0.00961 -0.1144 0.3399 1.0000
8.750 1.4217 0.01630 0.01016 -0.1123 0.3298 1.0000
9.000 1.4371 0.01683 0.01068 -0.1106 0.3196 1.0000
9.250 1.4495 0.01751 0.01132 -0.1085 0.3097 1.0000
9.500 1.4611 0.01826 0.01203 -0.1063 0.2966 1.0000
9.750 1.4704 0.01915 0.01285 -0.1040 0.2812 1.0000
10.000 1.4802 0.02005 0.01371 -0.1018 0.2672 1.0000
10.250 1.4879 0.02111 0.01471 -0.0994 0.2521 1.0000
10.500 1.4934 0.02233 0.01586 -0.0969 0.2353 1.0000
10.750 1.4963 0.02377 0.01721 -0.0943 0.2168 1.0000
11.000 1.4955 0.02553 0.01885 -0.0915 0.1961 1.0000
11.250 1.4970 0.02723 0.02049 -0.0891 0.1810 1.0000
11.500 1.5008 0.02885 0.02207 -0.0871 0.1709 1.0000
11.750 1.5076 0.03032 0.02355 -0.0854 0.1641 1.0000
12.000 1.5136 0.03191 0.02513 -0.0838 0.1580 1.0000
12.250 1.5205 0.03347 0.02671 -0.0824 0.1532 1.0000
12.500 1.5285 0.03499 0.02827 -0.0811 0.1487 1.0000
12.750 1.5344 0.03672 0.03001 -0.0798 0.1443 1.0000
13.000 1.5399 0.03852 0.03184 -0.0785 0.1403 1.0000
13.250 1.5478 0.04016 0.03352 -0.0775 0.1365 1.0000
13.500 1.5541 0.04195 0.03535 -0.0764 0.1326 1.0000
13.750 1.5576 0.04405 0.03748 -0.0753 0.1289 1.0000
14.000 1.5638 0.04593 0.03940 -0.0744 0.1256 1.0000
14.250 1.5689 0.04796 0.04147 -0.0735 0.1209 1.0000
14.500 1.5714 0.05028 0.04382 -0.0726 0.1170 1.0000
14.750 1.5756 0.05246 0.04604 -0.0719 0.1134 1.0000
15.000 1.5789 0.05479 0.04842 -0.0712 0.1091 1.0000
15.250 1.5794 0.05747 0.05111 -0.0705 0.1047 1.0000
15.500 1.5825 0.05991 0.05360 -0.0700 0.1004 1.0000
15.750 1.5816 0.06285 0.05657 -0.0696 0.0950 1.0000
16.000 1.5819 0.06570 0.05945 -0.0692 0.0900 1.0000
16.250 1.5794 0.06893 0.06269 -0.0689 0.0845 1.0000
16.500 1.5779 0.07210 0.06589 -0.0687 0.0790 1.0000
16.750 1.5745 0.07556 0.06937 -0.0687 0.0741 1.0000
17.000 1.5720 0.07893 0.07277 -0.0687 0.0699 1.0000
17.250 1.5687 0.08246 0.07634 -0.0688 0.0665 1.0000
17.500 1.5662 0.08594 0.07987 -0.0690 0.0636 1.0000
17.750 1.5630 0.08956 0.08351 -0.0694 0.0611 1.0000
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