GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Reynolds number: 500,000 Max Cl/Cd: 101.67 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe217-il-500000.txt Download as CSV file: xf-goe217-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 217 (MVA MK.12) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1680 0.10603 0.10359 -0.0607 0.9656 0.0441
-11.250 -0.2454 0.05853 0.05559 -0.0984 0.8788 0.0511
-11.000 -0.2898 0.04968 0.04650 -0.1061 0.8614 0.0511
-10.750 -0.3240 0.04341 0.03999 -0.1125 0.8427 0.0511
-10.500 -0.3483 0.03612 0.03209 -0.1331 0.8244 0.0513
-10.250 -0.3350 0.03251 0.02868 -0.1253 0.8101 0.0522
-10.000 -0.3173 0.03057 0.02672 -0.1246 0.7934 0.0527
-9.750 -0.2997 0.02834 0.02439 -0.1268 0.7775 0.0533
-9.250 -0.2545 0.02179 0.01703 -0.1437 0.7476 0.0581
-9.000 -0.2315 0.02030 0.01553 -0.1437 0.7341 0.0589
-8.750 -0.1993 0.01874 0.01336 -0.1500 0.7192 0.0637
-8.500 -0.1773 0.01707 0.01186 -0.1491 0.7074 0.0648
-8.250 -0.1511 0.01603 0.01075 -0.1497 0.6943 0.0666
-8.000 -0.1193 0.02318 0.01689 -0.1567 0.6983 0.0471
-7.750 -0.0868 0.02221 0.01550 -0.1571 0.6851 0.0413
-7.250 -0.0325 0.02038 0.01363 -0.1564 0.6589 0.0407
-7.000 -0.0046 0.01964 0.01282 -0.1562 0.6467 0.0405
-6.750 0.0241 0.01897 0.01212 -0.1563 0.6345 0.0404
-6.500 0.0527 0.01842 0.01149 -0.1563 0.6231 0.0404
-6.250 0.0820 0.01789 0.01093 -0.1564 0.6118 0.0404
-6.000 0.1118 0.01749 0.01045 -0.1567 0.6012 0.0406
-5.750 0.1428 0.01713 0.01002 -0.1573 0.5911 0.0409
-5.500 0.1734 0.01686 0.00963 -0.1578 0.5811 0.0412
-5.250 0.2032 0.01634 0.00915 -0.1581 0.5727 0.0413
-5.000 0.2337 0.01590 0.00869 -0.1586 0.5639 0.0416
-4.750 0.2658 0.01547 0.00825 -0.1596 0.5562 0.0419
-4.500 0.2990 0.01506 0.00783 -0.1609 0.5490 0.0424
-4.250 0.3322 0.01473 0.00743 -0.1621 0.5420 0.0429
-4.000 0.3654 0.01443 0.00708 -0.1634 0.5357 0.0435
-3.750 0.3989 0.01411 0.00673 -0.1646 0.5300 0.0441
-3.500 0.4319 0.01385 0.00641 -0.1657 0.5242 0.0447
-3.250 0.4642 0.01368 0.00615 -0.1666 0.5186 0.0454
-3.000 0.4964 0.01353 0.00594 -0.1674 0.5137 0.0461
-2.750 0.5300 0.01320 0.00559 -0.1687 0.5091 0.0476
-2.500 0.5620 0.01305 0.00539 -0.1694 0.5043 0.0494
-2.250 0.5932 0.01299 0.00525 -0.1699 0.4996 0.0512
-2.000 0.6244 0.01298 0.00514 -0.1705 0.4946 0.0540
-1.750 0.6562 0.01285 0.00503 -0.1710 0.4916 0.0604
-1.500 0.6934 0.01196 0.00467 -0.1737 0.4880 0.2351
-1.250 0.7253 0.01175 0.00464 -0.1746 0.4844 0.2924
-1.000 0.7560 0.01172 0.00469 -0.1750 0.4809 0.3357
-0.750 0.7859 0.01181 0.00480 -0.1752 0.4773 0.3643
-0.500 0.8156 0.01201 0.00498 -0.1753 0.4733 0.3844
-0.250 0.8455 0.01207 0.00510 -0.1754 0.4709 0.3991
0.000 0.8752 0.01217 0.00522 -0.1755 0.4679 0.4107
0.250 0.9047 0.01229 0.00534 -0.1755 0.4648 0.4207
0.500 0.9339 0.01241 0.00545 -0.1755 0.4609 0.4303
0.750 0.9626 0.01261 0.00561 -0.1754 0.4563 0.4387
1.000 0.9915 0.01285 0.00579 -0.1753 0.4519 0.4467
1.250 1.0205 0.01291 0.00592 -0.1753 0.4488 0.4538
1.500 1.0495 0.01301 0.00605 -0.1753 0.4452 0.4590
1.750 1.0785 0.01312 0.00614 -0.1752 0.4415 0.4639
2.000 1.1072 0.01328 0.00624 -0.1752 0.4378 0.4682
2.250 1.1355 0.01349 0.00640 -0.1751 0.4335 0.4729
2.500 1.1641 0.01357 0.00654 -0.1750 0.4304 0.4772
2.750 1.1927 0.01366 0.00667 -0.1750 0.4272 0.4814
3.000 1.2213 0.01377 0.00679 -0.1749 0.4239 0.4856
3.250 1.2497 0.01391 0.00691 -0.1749 0.4208 0.4894
3.500 1.2778 0.01405 0.00703 -0.1748 0.4175 0.4933
3.750 1.3051 0.01431 0.00726 -0.1746 0.4134 0.4983
4.000 1.3329 0.01442 0.00746 -0.1744 0.4106 0.5035
4.250 1.3608 0.01454 0.00762 -0.1742 0.4072 0.5088
4.500 1.3886 0.01467 0.00776 -0.1741 0.4037 0.5127
4.750 1.4160 0.01477 0.00787 -0.1739 0.4000 0.5163
5.000 1.4425 0.01497 0.00804 -0.1736 0.3958 0.5196
5.250 1.4694 0.01513 0.00825 -0.1733 0.3919 0.5231
5.500 1.4965 0.01522 0.00841 -0.1731 0.3878 0.5268
5.750 1.5232 0.01535 0.00856 -0.1728 0.3831 0.5303
6.000 1.5489 0.01555 0.00872 -0.1724 0.3784 0.5335
6.250 1.5746 0.01576 0.00893 -0.1720 0.3734 0.5365
6.500 1.6009 0.01583 0.00909 -0.1717 0.3675 0.5404
6.750 1.6252 0.01603 0.00929 -0.1710 0.3606 0.5436
7.000 1.6495 0.01625 0.00953 -0.1704 0.3535 0.5469
7.250 1.6735 0.01646 0.00975 -0.1697 0.3443 0.5503
7.500 1.6961 0.01675 0.01002 -0.1688 0.3341 0.5538
7.750 1.7164 0.01714 0.01034 -0.1676 0.3210 0.5571
8.000 1.7350 0.01758 0.01074 -0.1661 0.3047 0.5606
8.250 1.7502 0.01818 0.01128 -0.1641 0.2855 0.5637
8.500 1.7601 0.01898 0.01198 -0.1613 0.2659 0.5666
8.750 1.7631 0.01988 0.01280 -0.1572 0.2506 0.5694
9.000 1.7693 0.02091 0.01378 -0.1540 0.2379 0.5725
9.250 1.7766 0.02197 0.01479 -0.1512 0.2277 0.5757
9.500 1.7852 0.02302 0.01583 -0.1488 0.2200 0.5788
9.750 1.7923 0.02421 0.01703 -0.1464 0.2133 0.5821
10.000 1.7993 0.02549 0.01833 -0.1441 0.2077 0.5852
10.250 1.8085 0.02669 0.01960 -0.1423 0.2030 0.5884
10.500 1.8138 0.02826 0.02118 -0.1403 0.1985 0.5917
10.750 1.8168 0.03010 0.02303 -0.1383 0.1944 0.5949
11.000 1.8272 0.03143 0.02443 -0.1371 0.1915 0.5984
11.250 1.8344 0.03308 0.02614 -0.1357 0.1883 0.6015
11.500 1.8381 0.03509 0.02822 -0.1343 0.1853 0.6045
11.750 1.8381 0.03753 0.03069 -0.1329 0.1823 0.6077
12.000 1.8393 0.03994 0.03316 -0.1317 0.1797 0.6112
12.250 1.8464 0.04184 0.03516 -0.1308 0.1777 0.6153
12.500 1.8503 0.04409 0.03748 -0.1299 0.1756 0.6187
12.750 1.8518 0.04660 0.04006 -0.1291 0.1734 0.6217
13.000 1.8511 0.04940 0.04293 -0.1282 0.1713 0.6246
13.250 1.8479 0.05251 0.04609 -0.1274 0.1692 0.6277
13.500 1.8425 0.05584 0.04946 -0.1265 0.1669 0.6309
13.750 1.8463 0.05833 0.05205 -0.1260 0.1654 0.6348
14.000 1.8492 0.06093 0.05474 -0.1256 0.1636 0.6384
14.250 1.8512 0.06364 0.05754 -0.1252 0.1619 0.6417
14.500 1.8507 0.06665 0.06063 -0.1248 0.1601 0.6452
14.750 1.8499 0.06970 0.06373 -0.1245 0.1583 0.6492
15.000 1.8470 0.07304 0.06711 -0.1242 0.1565 0.6531
15.250 1.8444 0.07624 0.07032 -0.1238 0.1543 0.6565
15.500 1.8461 0.07909 0.07328 -0.1237 0.1528 0.6600
15.750 1.8490 0.08182 0.07611 -0.1236 0.1512 0.6639
16.000 1.8496 0.08485 0.07923 -0.1236 0.1494 0.6681
16.250 1.8507 0.08781 0.08225 -0.1236 0.1475 0.6721
16.500 1.8499 0.09102 0.08552 -0.1238 0.1457 0.6757
16.750 1.8492 0.09417 0.08870 -0.1239 0.1438 0.6796
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