GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 50,000 Max Cl/Cd: 38.78 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe239-il-50000-n5.txt Download as CSV file: xf-goe239-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 239 (MVA H.31) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3036 0.10845 0.10215 -0.0262 1.0000 0.1330
-7.500 -0.3150 0.10720 0.10101 -0.0239 1.0000 0.1345
-7.250 -0.3291 0.10611 0.10002 -0.0216 1.0000 0.1357
-7.000 -0.3282 0.10365 0.09762 -0.0307 0.9910 0.1395
-6.750 -0.3071 0.09452 0.08838 -0.0367 0.9850 0.0980
-6.250 -0.2611 0.07999 0.07362 -0.0596 0.9656 0.0809
-6.000 -0.2359 0.07534 0.06890 -0.0649 0.9578 0.0803
-5.750 -0.1991 0.06740 0.06075 -0.0785 0.9497 0.0810
-5.500 -0.1647 0.06004 0.05311 -0.0890 0.9408 0.0811
-5.250 -0.1199 0.05276 0.04540 -0.1003 0.9347 0.0809
-5.000 -0.0848 0.04826 0.04062 -0.1064 0.9258 0.0823
-4.750 -0.0454 0.04596 0.03821 -0.1107 0.9195 0.0858
-4.500 -0.0029 0.04127 0.03294 -0.1179 0.9108 0.0879
-4.250 0.0471 0.03706 0.02798 -0.1251 0.9050 0.0900
-4.000 0.0905 0.03429 0.02446 -0.1297 0.8971 0.0942
-3.750 0.1311 0.03255 0.02251 -0.1328 0.8895 0.0990
-3.500 0.1693 0.03108 0.02075 -0.1351 0.8809 0.1033
-3.250 0.2091 0.02968 0.01892 -0.1374 0.8727 0.1090
-3.000 0.2417 0.02877 0.01800 -0.1384 0.8619 0.1170
-2.750 0.2819 0.02768 0.01672 -0.1405 0.8544 0.1273
-2.500 0.3122 0.02709 0.01610 -0.1409 0.8420 0.1406
-2.250 0.3450 0.02662 0.01569 -0.1417 0.8308 0.1599
-2.000 0.3823 0.02609 0.01515 -0.1430 0.8220 0.1983
-1.750 0.4113 0.02593 0.01506 -0.1430 0.8088 0.2477
-1.500 0.4403 0.02597 0.01511 -0.1429 0.7965 0.2967
-1.250 0.4718 0.02594 0.01504 -0.1432 0.7865 0.3371
-1.000 0.5011 0.02589 0.01490 -0.1431 0.7751 0.3706
-0.750 0.5279 0.02588 0.01484 -0.1427 0.7629 0.4035
-0.500 0.5573 0.02568 0.01460 -0.1427 0.7528 0.4327
-0.250 0.5876 0.02545 0.01428 -0.1428 0.7431 0.4549
0.000 0.6145 0.02539 0.01416 -0.1425 0.7318 0.4712
0.250 0.6452 0.02514 0.01386 -0.1427 0.7234 0.4895
0.500 0.6721 0.02505 0.01382 -0.1424 0.7131 0.5113
0.750 0.6993 0.02496 0.01381 -0.1421 0.7035 0.5412
1.000 0.7279 0.02462 0.01365 -0.1418 0.6954 0.5919
1.500 0.7780 0.02405 0.01339 -0.1397 0.6780 1.0000
1.750 0.8033 0.02451 0.01368 -0.1394 0.6675 1.0000
2.000 0.8329 0.02471 0.01368 -0.1394 0.6593 1.0000
2.250 0.8602 0.02504 0.01386 -0.1392 0.6500 1.0000
2.500 0.8872 0.02538 0.01409 -0.1389 0.6411 1.0000
2.750 0.9160 0.02562 0.01420 -0.1388 0.6326 1.0000
3.000 0.9410 0.02609 0.01462 -0.1383 0.6232 1.0000
3.250 0.9711 0.02627 0.01468 -0.1383 0.6153 1.0000
3.500 0.9941 0.02685 0.01525 -0.1376 0.6053 1.0000
3.750 1.0244 0.02704 0.01533 -0.1376 0.5977 1.0000
4.000 1.0463 0.02769 0.01602 -0.1368 0.5876 1.0000
4.250 1.0739 0.02806 0.01633 -0.1365 0.5793 1.0000
4.500 1.0976 0.02863 0.01694 -0.1359 0.5698 1.0000
4.750 1.1227 0.02915 0.01746 -0.1354 0.5612 1.0000
5.000 1.1476 0.02968 0.01802 -0.1348 0.5523 1.0000
5.250 1.1704 0.03034 0.01874 -0.1341 0.5432 1.0000
5.500 1.1961 0.03084 0.01927 -0.1336 0.5347 1.0000
5.750 1.2166 0.03165 0.02018 -0.1326 0.5254 1.0000
6.000 1.2428 0.03214 0.02070 -0.1322 0.5172 1.0000
6.250 1.2607 0.03310 0.02182 -0.1309 0.5078 1.0000
6.500 1.2872 0.03359 0.02235 -0.1305 0.5000 1.0000
6.750 1.3022 0.03470 0.02364 -0.1289 0.4902 1.0000
7.000 1.3291 0.03515 0.02416 -0.1286 0.4827 1.0000
7.250 1.3405 0.03646 0.02569 -0.1266 0.4728 1.0000
7.500 1.3676 0.03691 0.02620 -0.1263 0.4659 1.0000
7.750 1.3752 0.03848 0.02801 -0.1240 0.4563 1.0000
8.000 1.4020 0.03890 0.02854 -0.1236 0.4496 1.0000
8.250 1.4056 0.04068 0.03057 -0.1209 0.4401 1.0000
8.500 1.4321 0.04108 0.03107 -0.1204 0.4337 1.0000
8.750 1.4306 0.04323 0.03348 -0.1173 0.4249 1.0000
9.000 1.4544 0.04378 0.03417 -0.1165 0.4187 1.0000
9.250 1.4488 0.04608 0.03672 -0.1131 0.4098 1.0000
9.500 1.4813 0.04554 0.03627 -0.1127 0.4020 1.0000
9.750 1.4592 0.04861 0.03955 -0.1077 0.3925 1.0000
10.000 1.4719 0.04905 0.04011 -0.1055 0.3828 1.0000
10.250 1.4948 0.04830 0.03940 -0.1037 0.3711 1.0000
10.500 1.4730 0.05162 0.04292 -0.0997 0.3609 1.0000
10.750 1.4719 0.05329 0.04474 -0.0971 0.3502 1.0000
11.000 1.4877 0.05337 0.04489 -0.0953 0.3393 1.0000
11.250 1.4759 0.05649 0.04819 -0.0930 0.3294 1.0000
11.500 1.4666 0.05960 0.05144 -0.0911 0.3195 1.0000
11.750 1.4754 0.06053 0.05246 -0.0894 0.3082 1.0000
12.000 1.4685 0.06352 0.05560 -0.0880 0.2973 1.0000
12.250 1.4480 0.06868 0.06094 -0.0873 0.2874 1.0000
12.500 1.4494 0.07085 0.06323 -0.0862 0.2761 1.0000
12.750 1.4537 0.07253 0.06501 -0.0850 0.2635 1.0000
13.000 1.4227 0.08003 0.07271 -0.0860 0.2531 1.0000
13.250 1.4106 0.08464 0.07749 -0.0862 0.2405 1.0000
13.500 1.4034 0.08850 0.08145 -0.0862 0.2268 1.0000
13.750 1.3950 0.09267 0.08572 -0.0865 0.2121 1.0000
14.000 1.3840 0.09744 0.09059 -0.0872 0.1964 1.0000
14.250 1.3736 0.10225 0.09546 -0.0881 0.1797 1.0000
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Polar data table (+)
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