GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 100,000 Max Cl/Cd: 55.2 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe309-il-100000-n5.txt Download as CSV file: xf-goe309-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 309 (MVA H.41) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3591 0.11056 0.10602 -0.0250 1.0000 0.0355
-8.500 -0.3560 0.10730 0.10282 -0.0272 1.0000 0.0355
-8.250 -0.3533 0.10355 0.09916 -0.0291 1.0000 0.0356
-8.000 -0.3411 0.09704 0.09264 -0.0253 1.0000 0.0368
-7.750 -0.3361 0.09365 0.08930 -0.0256 1.0000 0.0374
-7.500 -0.3336 0.09057 0.08629 -0.0264 1.0000 0.0378
-7.250 -0.3305 0.08749 0.08326 -0.0276 1.0000 0.0383
-7.000 -0.3289 0.08458 0.08041 -0.0285 1.0000 0.0385
-6.750 -0.3304 0.08193 0.07783 -0.0287 1.0000 0.0385
-6.500 -0.3341 0.07941 0.07537 -0.0287 0.9996 0.0380
-6.250 -0.3065 0.07394 0.06979 -0.0353 0.9889 0.0328
-6.000 -0.2749 0.06858 0.06430 -0.0432 0.9783 0.0336
-5.750 -0.2440 0.06335 0.05891 -0.0496 0.9670 0.0340
-5.500 -0.2169 0.05851 0.05394 -0.0539 0.9550 0.0333
-5.250 -0.1890 0.05378 0.04901 -0.0577 0.9418 0.0330
-5.000 -0.1599 0.04895 0.04388 -0.0611 0.9282 0.0338
-4.750 -0.1317 0.04376 0.03832 -0.0636 0.9145 0.0364
-4.500 -0.1087 0.04105 0.03544 -0.0643 0.9009 0.0378
-4.250 -0.0834 0.03782 0.03192 -0.0649 0.8879 0.0390
-4.000 -0.0574 0.03532 0.02911 -0.0652 0.8756 0.0433
-3.750 -0.0303 0.03152 0.02478 -0.0652 0.8645 0.0453
-3.500 -0.0026 0.02800 0.02048 -0.0646 0.8533 0.0482
-3.250 0.0217 0.02640 0.01869 -0.0644 0.8412 0.0514
-3.000 0.0482 0.02460 0.01649 -0.0639 0.8299 0.0529
-2.750 0.0755 0.02300 0.01448 -0.0634 0.8191 0.0546
-2.500 0.1029 0.02191 0.01300 -0.0629 0.8085 0.0590
-2.250 0.1304 0.02067 0.01136 -0.0624 0.7972 0.0604
-2.000 0.1579 0.01961 0.01001 -0.0619 0.7861 0.0611
-1.750 0.1850 0.01872 0.00891 -0.0614 0.7755 0.0621
-1.500 0.2116 0.01800 0.00810 -0.0609 0.7654 0.0640
-1.250 0.2381 0.01751 0.00753 -0.0604 0.7538 0.0668
-1.000 0.2645 0.01706 0.00700 -0.0599 0.7427 0.0711
-0.750 0.2907 0.01667 0.00652 -0.0593 0.7321 0.0772
-0.500 0.3172 0.01639 0.00614 -0.0587 0.7219 0.0886
-0.250 0.3437 0.01618 0.00594 -0.0583 0.7103 0.1109
0.000 0.3702 0.01594 0.00570 -0.0580 0.6992 0.1402
0.250 0.3963 0.01574 0.00552 -0.0576 0.6886 0.1706
0.500 0.4215 0.01545 0.00549 -0.0571 0.6781 0.2547
1.000 0.5163 0.01389 0.00537 -0.0645 0.6539 1.0000
1.250 0.5409 0.01401 0.00533 -0.0638 0.6429 1.0000
1.500 0.5655 0.01414 0.00530 -0.0631 0.6323 1.0000
1.750 0.5900 0.01428 0.00532 -0.0624 0.6211 1.0000
2.000 0.6144 0.01443 0.00537 -0.0617 0.6097 1.0000
2.250 0.6389 0.01458 0.00544 -0.0610 0.5985 1.0000
2.500 0.6630 0.01473 0.00548 -0.0603 0.5859 1.0000
2.750 0.6869 0.01487 0.00552 -0.0594 0.5708 1.0000
3.000 0.7106 0.01501 0.00558 -0.0586 0.5548 1.0000
3.250 0.7344 0.01518 0.00566 -0.0578 0.5395 1.0000
3.500 0.7585 0.01538 0.00579 -0.0571 0.5267 1.0000
3.750 0.7828 0.01559 0.00595 -0.0564 0.5159 1.0000
4.000 0.8072 0.01582 0.00618 -0.0558 0.5046 1.0000
4.250 0.8315 0.01606 0.00642 -0.0552 0.4934 1.0000
4.500 0.8558 0.01631 0.00668 -0.0547 0.4827 1.0000
4.750 0.8801 0.01658 0.00696 -0.0541 0.4727 1.0000
5.000 0.9043 0.01685 0.00728 -0.0535 0.4615 1.0000
5.250 0.9283 0.01714 0.00761 -0.0529 0.4499 1.0000
5.500 0.9522 0.01744 0.00796 -0.0523 0.4380 1.0000
5.750 0.9756 0.01775 0.00834 -0.0516 0.4238 1.0000
6.000 0.9965 0.01806 0.00861 -0.0505 0.3970 1.0000
6.250 1.0174 0.01843 0.00895 -0.0495 0.3692 1.0000
6.500 1.0383 0.01886 0.00935 -0.0485 0.3417 1.0000
6.750 1.0584 0.01936 0.00985 -0.0474 0.3092 1.0000
7.000 1.0755 0.02011 0.01038 -0.0461 0.2666 1.0000
7.250 1.0889 0.02125 0.01116 -0.0444 0.2164 1.0000
7.500 1.1050 0.02223 0.01200 -0.0430 0.1864 1.0000
7.750 1.1203 0.02329 0.01291 -0.0415 0.1513 1.0000
8.250 1.1260 0.02753 0.01626 -0.0359 0.0260 1.0000
8.500 1.1381 0.02873 0.01767 -0.0339 0.0239 1.0000
8.750 1.1475 0.03010 0.01923 -0.0318 0.0219 1.0000
9.000 1.1545 0.03146 0.02078 -0.0293 0.0206 1.0000
9.250 1.1609 0.03284 0.02238 -0.0270 0.0196 1.0000
9.500 1.1656 0.03445 0.02420 -0.0248 0.0191 1.0000
9.750 1.1685 0.03629 0.02625 -0.0228 0.0187 1.0000
10.000 1.1695 0.03840 0.02857 -0.0212 0.0183 1.0000
10.250 1.1688 0.04081 0.03119 -0.0198 0.0181 1.0000
10.500 1.1667 0.04352 0.03410 -0.0189 0.0178 1.0000
10.750 1.1634 0.04651 0.03728 -0.0183 0.0175 1.0000
11.000 1.1594 0.04973 0.04068 -0.0180 0.0172 1.0000
11.250 1.1548 0.05315 0.04425 -0.0179 0.0167 1.0000
11.500 1.1501 0.05667 0.04793 -0.0180 0.0163 1.0000
11.750 1.1457 0.06023 0.05168 -0.0181 0.0158 1.0000
12.000 1.1422 0.06369 0.05525 -0.0182 0.0154 1.0000
12.250 1.1404 0.06691 0.05857 -0.0180 0.0150 1.0000
12.500 1.1418 0.06964 0.06137 -0.0175 0.0148 1.0000
12.750 1.1467 0.07187 0.06367 -0.0164 0.0145 1.0000
13.000 1.1553 0.07370 0.06555 -0.0150 0.0143 1.0000
13.250 1.1657 0.07550 0.06742 -0.0135 0.0142 1.0000
13.500 1.1755 0.07760 0.06964 -0.0122 0.0140 1.0000
13.750 1.1824 0.08022 0.07241 -0.0114 0.0140 1.0000
14.000 1.1861 0.08333 0.07570 -0.0111 0.0139 1.0000
14.250 1.1866 0.08690 0.07946 -0.0113 0.0139 1.0000
14.500 1.1842 0.09089 0.08365 -0.0119 0.0139 1.0000
14.750 1.1795 0.09525 0.08821 -0.0129 0.0138 1.0000
15.000 1.1729 0.09998 0.09314 -0.0144 0.0137 1.0000
15.250 1.1648 0.10507 0.09842 -0.0163 0.0136 1.0000
15.500 1.1555 0.11050 0.10405 -0.0187 0.0135 1.0000
15.750 1.1452 0.11627 0.11002 -0.0216 0.0135 1.0000
16.000 1.1342 0.12241 0.11636 -0.0250 0.0135 1.0000
16.250 1.1228 0.12893 0.12307 -0.0288 0.0135 1.0000
16.500 1.1110 0.13591 0.13024 -0.0332 0.0136 1.0000
16.750 1.0989 0.14341 0.13793 -0.0382 0.0137 1.0000
17.000 1.0862 0.15157 0.14628 -0.0436 0.0139 1.0000
17.250 1.0730 0.16050 0.15539 -0.0497 0.0142 1.0000
17.500 1.0559 0.17163 0.16670 -0.0571 0.0148 1.0000
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