GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Reynolds number: 100,000 Max Cl/Cd: 40.18 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe217-il-100000.txt Download as CSV file: xf-goe217-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0776 0.11308 0.10856 -0.0609 0.9639 0.1841
-9.250 -0.0374 0.10808 0.10354 -0.0639 0.9536 0.1868
-9.000 -0.2557 0.06097 0.05596 -0.1114 0.9295 0.1016
-8.750 -0.2445 0.04433 0.03793 -0.1465 0.9123 0.0926
-8.500 -0.2110 0.04098 0.03435 -0.1507 0.8993 0.0919
-8.250 -0.1730 0.03790 0.03095 -0.1553 0.8880 0.0915
-8.000 -0.1358 0.03537 0.02813 -0.1586 0.8761 0.0908
-7.750 -0.1049 0.03353 0.02605 -0.1599 0.8611 0.0899
-7.500 -0.0701 0.03180 0.02407 -0.1613 0.8499 0.0892
-7.250 -0.0419 0.03057 0.02267 -0.1614 0.8343 0.0887
-7.000 -0.0137 0.02954 0.02149 -0.1612 0.8200 0.0885
-6.750 0.0155 0.02857 0.02038 -0.1606 0.8081 0.0885
-6.500 0.0405 0.02792 0.01970 -0.1595 0.7930 0.0888
-6.250 0.0672 0.02731 0.01902 -0.1582 0.7817 0.0893
-6.000 0.0916 0.02691 0.01863 -0.1567 0.7684 0.0899
-5.750 0.1173 0.02660 0.01830 -0.1553 0.7579 0.0910
-5.500 0.1434 0.02638 0.01803 -0.1543 0.7459 0.0928
-5.250 0.1680 0.02620 0.01796 -0.1527 0.7364 0.0951
-5.000 0.1960 0.02597 0.01776 -0.1526 0.7247 0.0977
-4.750 0.2299 0.02553 0.01716 -0.1538 0.7165 0.1005
-4.500 0.2645 0.02495 0.01660 -0.1564 0.7051 0.1040
-4.250 0.3035 0.02418 0.01568 -0.1595 0.6969 0.1106
-4.000 0.3493 0.02271 0.01471 -0.1658 0.6884 0.1838
-3.750 0.3852 0.02243 0.01461 -0.1681 0.6796 0.2618
-3.500 0.4187 0.02258 0.01475 -0.1689 0.6728 0.3078
-3.250 0.4472 0.02324 0.01544 -0.1687 0.6650 0.3371
-3.000 0.4741 0.02398 0.01617 -0.1678 0.6572 0.3570
-2.750 0.5003 0.02481 0.01695 -0.1664 0.6514 0.3719
-2.500 0.5276 0.02564 0.01769 -0.1655 0.6460 0.3867
-2.250 0.5465 0.02696 0.01919 -0.1626 0.6392 0.3957
-2.000 0.5718 0.02779 0.01999 -0.1614 0.6335 0.4080
-1.750 0.5922 0.02889 0.02112 -0.1583 0.6289 0.4147
-1.500 0.6215 0.02944 0.02154 -0.1582 0.6243 0.4281
-1.250 0.6349 0.03088 0.02320 -0.1541 0.6181 0.4333
-1.000 0.6622 0.03151 0.02379 -0.1539 0.6126 0.4491
-0.750 0.6775 0.03262 0.02497 -0.1497 0.6086 0.4540
-0.500 0.7177 0.03235 0.02447 -0.1531 0.6049 0.4701
-0.250 0.7369 0.03308 0.02529 -0.1510 0.6009 0.4737
0.000 0.7573 0.03378 0.02611 -0.1499 0.5955 0.4802
0.250 0.7906 0.03387 0.02611 -0.1520 0.5905 0.4940
0.500 0.8125 0.03431 0.02657 -0.1502 0.5866 0.4998
0.750 0.8498 0.03435 0.02644 -0.1527 0.5833 0.5151
1.000 0.8700 0.03501 0.02714 -0.1508 0.5802 0.5203
1.250 0.8873 0.03612 0.02843 -0.1502 0.5748 0.5289
1.500 0.9128 0.03673 0.02905 -0.1507 0.5698 0.5395
1.750 0.9352 0.03720 0.02954 -0.1495 0.5660 0.5473
2.000 0.9694 0.03739 0.02963 -0.1511 0.5627 0.5598
2.250 0.9956 0.03758 0.02978 -0.1500 0.5598 0.5673
2.500 1.0070 0.03946 0.03185 -0.1497 0.5528 0.5768
2.750 1.0275 0.03978 0.03222 -0.1485 0.5464 0.5841
3.000 1.0663 0.03890 0.03117 -0.1492 0.5412 0.5959
3.250 1.0981 0.03855 0.03072 -0.1491 0.5361 0.6052
3.500 1.1039 0.04018 0.03258 -0.1472 0.5279 0.6122
3.750 1.1368 0.04000 0.03233 -0.1479 0.5226 0.6218
4.000 1.1718 0.03939 0.03162 -0.1482 0.5186 0.6307
4.250 1.1994 0.04003 0.03223 -0.1490 0.5134 0.6385
4.500 1.2013 0.04173 0.03418 -0.1464 0.5057 0.6429
4.750 1.2356 0.04132 0.03371 -0.1471 0.5007 0.6509
5.000 1.2785 0.04040 0.03263 -0.1487 0.4967 0.6583
5.250 1.2879 0.04178 0.03416 -0.1469 0.4900 0.6630
5.500 1.3022 0.04279 0.03527 -0.1458 0.4826 0.6688
5.750 1.3437 0.04176 0.03413 -0.1471 0.4778 0.6759
6.000 1.3923 0.04049 0.03265 -0.1493 0.4739 0.6828
6.250 1.3780 0.04322 0.03573 -0.1451 0.4640 0.6858
6.500 1.4160 0.04231 0.03474 -0.1460 0.4582 0.6924
6.750 1.4679 0.04068 0.03289 -0.1484 0.4538 0.7005
7.000 1.4579 0.04292 0.03542 -0.1445 0.4440 0.7036
7.250 1.4955 0.04194 0.03437 -0.1453 0.4376 0.7090
7.500 1.5511 0.04017 0.03232 -0.1482 0.4326 0.7173
7.750 1.5347 0.04233 0.03482 -0.1431 0.4217 0.7206
8.000 1.5842 0.04057 0.03288 -0.1452 0.4154 0.7280
8.250 1.5845 0.04176 0.03423 -0.1419 0.4057 0.7320
8.500 1.6186 0.04098 0.03333 -0.1424 0.3976 0.7380
8.750 1.6326 0.04128 0.03368 -0.1405 0.3887 0.7432
9.000 1.6502 0.04122 0.03359 -0.1389 0.3795 0.7497
9.250 1.6662 0.04147 0.03381 -0.1373 0.3706 0.7557
9.500 1.6698 0.04193 0.03429 -0.1340 0.3617 0.7606
9.750 1.6857 0.04218 0.03449 -0.1324 0.3533 0.7666
10.000 1.6834 0.04349 0.03586 -0.1292 0.3444 0.7713
10.250 1.7075 0.04346 0.03571 -0.1286 0.3369 0.7787
10.500 1.6901 0.04604 0.03848 -0.1246 0.3288 0.7834
10.750 1.7405 0.04446 0.03661 -0.1262 0.3220 0.7952
11.000 1.6995 0.04898 0.04149 -0.1212 0.3150 0.7979
11.250 1.7195 0.04935 0.04180 -0.1204 0.3085 0.8080
11.500 1.7336 0.05030 0.04276 -0.1194 0.3028 0.8189
11.750 1.7055 0.05477 0.04750 -0.1167 0.2969 0.8252
12.000 1.7281 0.05451 0.04725 -0.1156 0.2917 0.8870
12.250 1.7457 0.05550 0.04818 -0.1151 0.2868 1.0000
12.500 1.6956 0.06280 0.05583 -0.1129 0.2821 1.0000
12.750 1.6997 0.06517 0.05823 -0.1123 0.2773 1.0000
13.000 1.7879 0.05967 0.05223 -0.1133 0.2722 1.0000
13.250 1.7095 0.07001 0.06310 -0.1113 0.2689 1.0000
13.500 1.0221 0.20349 0.19778 -0.1680 0.3000 0.7565
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Polar data table (+)
Polar graphs
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