GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il) Reynolds number: 100,000 Max Cl/Cd: 42.51 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe222-il-100000.txt Download as CSV file: xf-goe222-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 222 (MVA H.33) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4212 0.07459 0.06985 -0.1083 0.9064 0.0927
-8.250 -0.4297 0.06990 0.06503 -0.1105 0.9029 0.0917
-8.000 -0.4316 0.06381 0.05864 -0.1159 0.8990 0.0905
-7.750 -0.4090 0.05684 0.05105 -0.1257 0.8956 0.0894
-7.500 -0.3674 0.05201 0.04551 -0.1345 0.8922 0.0901
-7.250 -0.3112 0.04871 0.04145 -0.1431 0.8893 0.0919
-7.000 -0.3024 0.04753 0.03997 -0.1419 0.8830 0.0924
-6.750 -0.2676 0.04560 0.03793 -0.1444 0.8781 0.0938
-6.500 -0.2175 0.04413 0.03640 -0.1487 0.8740 0.0966
-6.250 -0.1994 0.04351 0.03569 -0.1480 0.8661 0.0992
-6.000 -0.1575 0.04249 0.03444 -0.1508 0.8603 0.1032
-5.750 -0.1042 0.04121 0.03320 -0.1551 0.8568 0.1078
-5.500 -0.0956 0.04112 0.03316 -0.1528 0.8482 0.1107
-5.250 -0.0533 0.04041 0.03239 -0.1555 0.8434 0.1185
-5.000 0.0007 0.03935 0.03145 -0.1603 0.8405 0.1338
-4.750 0.0136 0.03927 0.03149 -0.1593 0.8315 0.1487
-4.500 0.0620 0.03884 0.03176 -0.1638 0.8269 0.2724
-4.250 0.1037 0.04014 0.03300 -0.1644 0.8234 0.3114
-4.000 0.1046 0.04134 0.03420 -0.1604 0.8122 0.3225
-3.750 0.1437 0.04207 0.03487 -0.1609 0.8082 0.3422
-3.500 0.1496 0.04323 0.03614 -0.1571 0.7975 0.3499
-3.250 0.1866 0.04354 0.03638 -0.1576 0.7927 0.3657
-3.000 0.2011 0.04443 0.03732 -0.1551 0.7835 0.3751
-2.750 0.2305 0.04473 0.03760 -0.1546 0.7773 0.3875
-2.500 0.2689 0.04482 0.03769 -0.1547 0.7742 0.4046
-2.250 0.2789 0.04566 0.03848 -0.1525 0.7619 0.4157
-2.000 0.3155 0.04532 0.03817 -0.1524 0.7582 0.4267
-1.750 0.3399 0.04545 0.03808 -0.1535 0.7473 0.4376
-1.500 0.3718 0.04505 0.03775 -0.1528 0.7424 0.4448
-1.250 0.4222 0.04392 0.03641 -0.1566 0.7400 0.4572
-1.000 0.4307 0.04472 0.03724 -0.1542 0.7271 0.4611
-0.750 0.4752 0.04375 0.03614 -0.1566 0.7238 0.4692
-0.500 0.5256 0.04240 0.03461 -0.1602 0.7221 0.4768
-0.250 0.5340 0.04334 0.03556 -0.1581 0.7081 0.4801
0.000 0.5800 0.04212 0.03423 -0.1605 0.7058 0.4875
0.250 0.6316 0.04057 0.03250 -0.1640 0.7045 0.4948
0.500 0.6791 0.03905 0.03094 -0.1661 0.7035 0.5002
0.750 0.6822 0.04052 0.03240 -0.1635 0.6883 0.5044
1.000 0.6947 0.04171 0.03352 -0.1625 0.6761 0.5098
1.250 0.7333 0.04080 0.03257 -0.1638 0.6726 0.5157
1.500 0.7785 0.03951 0.03123 -0.1658 0.6709 0.5221
1.750 0.8292 0.03812 0.02970 -0.1689 0.6695 0.5306
2.000 0.8785 0.03667 0.02825 -0.1715 0.6682 0.5383
2.250 0.9383 0.03522 0.02666 -0.1763 0.6671 0.5484
2.500 0.9203 0.03743 0.02895 -0.1702 0.6519 0.5509
2.750 0.9723 0.03600 0.02750 -0.1733 0.6506 0.5599
3.000 0.9516 0.03911 0.03065 -0.1678 0.6358 0.5637
3.250 0.9673 0.04006 0.03164 -0.1667 0.6289 0.5704
3.500 1.0381 0.03733 0.02882 -0.1719 0.6311 0.5844
3.750 0.9766 0.04388 0.03549 -0.1628 0.6111 0.5839
4.000 1.0429 0.04069 0.03231 -0.1664 0.6129 0.5970
4.250 1.1209 0.03712 0.02869 -0.1721 0.6146 0.6144
4.500 1.0467 0.04477 0.03649 -0.1618 0.5954 0.6120
4.750 1.1161 0.04110 0.03281 -0.1655 0.5963 0.6310
5.000 1.2040 0.03673 0.02837 -0.1721 0.5980 0.6556
5.250 1.1719 0.04049 0.03226 -0.1653 0.5856 0.6613
5.500 1.2375 0.03753 0.02932 -0.1692 0.5845 0.6910
5.750 1.3085 0.03454 0.02644 -0.1743 0.5829 0.7348
6.000 1.2564 0.03911 0.03123 -0.1646 0.5698 0.7468
6.250 1.3113 0.03608 0.02844 -0.1667 0.5681 1.0000
6.500 1.3859 0.03400 0.02612 -0.1733 0.5661 1.0000
6.750 1.3128 0.04009 0.03242 -0.1614 0.5533 1.0000
7.000 1.3801 0.03772 0.02991 -0.1659 0.5517 1.0000
7.250 1.4578 0.03527 0.02729 -0.1723 0.5496 1.0000
7.500 1.3696 0.04236 0.03463 -0.1590 0.5367 1.0000
7.750 1.4510 0.03883 0.03097 -0.1646 0.5350 1.0000
8.000 1.3612 0.04739 0.03976 -0.1530 0.5209 1.0000
8.250 1.4490 0.04261 0.03486 -0.1583 0.5200 1.0000
8.500 1.5388 0.03889 0.03100 -0.1652 0.5174 1.0000
8.750 1.3272 0.05801 0.05056 -0.1443 0.4929 1.0000
9.000 1.3836 0.05470 0.04722 -0.1455 0.4909 1.0000
9.250 1.6412 0.03861 0.03068 -0.1677 0.4983 1.0000
9.500 1.2745 0.07214 0.06489 -0.1371 0.4569 1.0000
9.750 1.6591 0.04051 0.03270 -0.1628 0.4823 1.0000
10.000 1.5811 0.04657 0.03903 -0.1510 0.4714 1.0000
10.250 1.6823 0.04222 0.03449 -0.1587 0.4655 1.0000
10.500 1.6221 0.04728 0.03980 -0.1491 0.4549 1.0000
10.750 1.7126 0.04364 0.03598 -0.1556 0.4479 1.0000
11.000 1.6534 0.04864 0.04122 -0.1463 0.4371 1.0000
11.250 1.7583 0.04429 0.03662 -0.1542 0.4293 1.0000
11.500 1.6781 0.05039 0.04303 -0.1429 0.4185 1.0000
11.750 1.7654 0.04690 0.03933 -0.1486 0.4107 1.0000
12.000 1.6909 0.05310 0.04583 -0.1387 0.4003 1.0000
12.250 1.7685 0.04993 0.04248 -0.1431 0.3932 1.0000
12.500 1.6862 0.05734 0.05022 -0.1337 0.3833 1.0000
12.750 1.7812 0.05261 0.04526 -0.1389 0.3774 1.0000
13.000 1.6528 0.06455 0.05764 -0.1277 0.3672 1.0000
13.250 1.7218 0.06073 0.05373 -0.1298 0.3625 1.0000
13.500 1.4440 0.09469 0.08815 -0.1204 0.3416 1.0000
13.750 1.5119 0.08831 0.08180 -0.1197 0.3413 1.0000
14.000 1.6100 0.07907 0.07254 -0.1203 0.3413 1.0000
14.250 1.4719 0.10019 0.09384 -0.1186 0.3275 1.0000
14.500 1.5461 0.09283 0.08652 -0.1177 0.3277 1.0000
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Polar data table (+)
Polar graphs
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