GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 100,000 Max Cl/Cd: 60.72 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe239-il-100000-n5.txt Download as CSV file: xf-goe239-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2721 0.11369 0.10884 -0.0375 1.0000 0.0608
-9.250 -0.2781 0.11197 0.10718 -0.0358 1.0000 0.0613
-9.000 -0.2845 0.11044 0.10572 -0.0338 1.0000 0.0624
-8.750 -0.2797 0.10713 0.10242 -0.0422 0.9926 0.0677
-8.500 -0.2722 0.10297 0.09827 -0.0495 0.9848 0.0682
-8.250 -0.2480 0.09641 0.09163 -0.0480 0.9832 0.0538
-8.000 -0.2369 0.09154 0.08675 -0.0528 0.9756 0.0510
-7.750 -0.2259 0.08741 0.08262 -0.0570 0.9666 0.0511
-7.500 -0.2104 0.08330 0.07850 -0.0620 0.9588 0.0524
-7.250 -0.1944 0.07850 0.07368 -0.0681 0.9511 0.0523
-7.000 -0.1786 0.07320 0.06836 -0.0750 0.9431 0.0515
-6.750 -0.1567 0.06744 0.06253 -0.0834 0.9362 0.0515
-6.500 -0.1345 0.06206 0.05709 -0.0914 0.9280 0.0531
-6.250 -0.1032 0.05369 0.04855 -0.1045 0.9211 0.0536
-6.000 -0.0566 0.03730 0.03122 -0.1284 0.9141 0.0541
-5.750 -0.0171 0.03156 0.02450 -0.1363 0.9081 0.0565
-5.500 0.0218 0.02848 0.02079 -0.1404 0.9039 0.0575
-5.250 0.0522 0.02675 0.01885 -0.1418 0.8968 0.0587
-5.000 0.0854 0.02541 0.01732 -0.1434 0.8902 0.0604
-4.750 0.1198 0.02426 0.01594 -0.1449 0.8841 0.0633
-4.500 0.1498 0.02316 0.01456 -0.1455 0.8753 0.0655
-4.250 0.1851 0.02199 0.01310 -0.1469 0.8694 0.0674
-4.000 0.2126 0.02113 0.01210 -0.1468 0.8592 0.0693
-3.750 0.2441 0.02034 0.01129 -0.1474 0.8512 0.0722
-3.500 0.2731 0.01978 0.01065 -0.1475 0.8407 0.0766
-3.250 0.3021 0.01925 0.00996 -0.1474 0.8296 0.0810
-3.000 0.3327 0.01856 0.00928 -0.1478 0.8196 0.0858
-2.750 0.3614 0.01810 0.00873 -0.1478 0.8072 0.0928
-2.500 0.3900 0.01760 0.00821 -0.1478 0.7940 0.1033
-2.250 0.4191 0.01709 0.00770 -0.1480 0.7802 0.1184
-2.000 0.4480 0.01659 0.00739 -0.1481 0.7657 0.1512
-1.750 0.4766 0.01639 0.00728 -0.1480 0.7506 0.2175
-1.500 0.5049 0.01634 0.00721 -0.1478 0.7351 0.2577
-1.250 0.5331 0.01634 0.00714 -0.1475 0.7194 0.2865
-1.000 0.5614 0.01639 0.00708 -0.1473 0.7040 0.3119
-0.750 0.5895 0.01644 0.00703 -0.1471 0.6896 0.3330
-0.500 0.6177 0.01648 0.00695 -0.1469 0.6765 0.3501
-0.250 0.6456 0.01651 0.00687 -0.1466 0.6639 0.3655
0.000 0.6731 0.01655 0.00683 -0.1464 0.6521 0.3816
0.250 0.7008 0.01658 0.00677 -0.1462 0.6417 0.3962
0.500 0.7286 0.01663 0.00670 -0.1460 0.6318 0.4095
0.750 0.7560 0.01668 0.00671 -0.1457 0.6220 0.4225
1.000 0.7836 0.01674 0.00669 -0.1455 0.6135 0.4378
1.250 0.8106 0.01680 0.00678 -0.1453 0.6042 0.4570
1.500 0.8379 0.01685 0.00686 -0.1451 0.5964 0.4841
1.750 0.8643 0.01684 0.00703 -0.1448 0.5877 0.5351
2.000 0.8840 0.01616 0.00701 -0.1426 0.5807 1.0000
2.250 0.9111 0.01644 0.00720 -0.1424 0.5722 1.0000
2.500 0.9389 0.01674 0.00732 -0.1423 0.5650 1.0000
2.750 0.9654 0.01703 0.00758 -0.1420 0.5567 1.0000
3.000 0.9928 0.01734 0.00776 -0.1419 0.5498 1.0000
3.250 1.0191 0.01765 0.00805 -0.1416 0.5422 1.0000
3.500 1.0458 0.01796 0.00831 -0.1414 0.5352 1.0000
3.750 1.0723 0.01829 0.00860 -0.1411 0.5284 1.0000
4.000 1.0983 0.01862 0.00893 -0.1408 0.5210 1.0000
4.250 1.1253 0.01896 0.00921 -0.1406 0.5149 1.0000
4.500 1.1502 0.01931 0.00963 -0.1401 0.5073 1.0000
4.750 1.1762 0.01965 0.00996 -0.1398 0.5007 1.0000
5.000 1.2012 0.02001 0.01038 -0.1393 0.4934 1.0000
5.250 1.2261 0.02035 0.01076 -0.1388 0.4856 1.0000
5.500 1.2510 0.02071 0.01115 -0.1383 0.4783 1.0000
5.750 1.2749 0.02107 0.01161 -0.1377 0.4701 1.0000
6.000 1.2996 0.02143 0.01200 -0.1371 0.4631 1.0000
6.250 1.3226 0.02182 0.01251 -0.1364 0.4546 1.0000
6.500 1.3468 0.02218 0.01290 -0.1357 0.4476 1.0000
6.750 1.3689 0.02259 0.01348 -0.1348 0.4385 1.0000
7.000 1.3916 0.02296 0.01390 -0.1340 0.4302 1.0000
7.250 1.4128 0.02334 0.01438 -0.1329 0.4200 1.0000
7.500 1.4331 0.02373 0.01490 -0.1316 0.4089 1.0000
7.750 1.4530 0.02411 0.01533 -0.1303 0.3980 1.0000
8.000 1.4722 0.02450 0.01576 -0.1289 0.3871 1.0000
8.250 1.4905 0.02500 0.01637 -0.1274 0.3757 1.0000
8.500 1.5081 0.02551 0.01697 -0.1258 0.3646 1.0000
8.750 1.5242 0.02606 0.01755 -0.1239 0.3530 1.0000
9.000 1.5389 0.02666 0.01817 -0.1219 0.3413 1.0000
9.250 1.5531 0.02735 0.01897 -0.1199 0.3301 1.0000
9.500 1.5665 0.02807 0.01978 -0.1178 0.3202 1.0000
9.750 1.5763 0.02884 0.02058 -0.1151 0.3103 1.0000
10.000 1.5851 0.02971 0.02158 -0.1124 0.2992 1.0000
10.250 1.5929 0.03068 0.02264 -0.1098 0.2883 1.0000
10.500 1.5996 0.03175 0.02378 -0.1071 0.2778 1.0000
10.750 1.6054 0.03295 0.02509 -0.1045 0.2665 1.0000
11.000 1.6089 0.03434 0.02660 -0.1019 0.2536 1.0000
11.250 1.6093 0.03601 0.02835 -0.0992 0.2386 1.0000
11.500 1.6068 0.03801 0.03040 -0.0966 0.2213 1.0000
12.000 1.5928 0.04332 0.03572 -0.0919 0.1741 1.0000
12.250 1.5781 0.04702 0.03930 -0.0898 0.1454 1.0000
12.500 1.5602 0.05137 0.04352 -0.0882 0.1273 1.0000
12.750 1.5439 0.05588 0.04801 -0.0872 0.1147 1.0000
13.000 1.5280 0.06064 0.05278 -0.0866 0.1054 1.0000
13.250 1.5159 0.06523 0.05746 -0.0863 0.0960 1.0000
13.500 1.5035 0.07003 0.06235 -0.0864 0.0883 1.0000
13.750 1.4904 0.07512 0.06753 -0.0868 0.0815 1.0000
14.000 1.4784 0.08019 0.07269 -0.0874 0.0761 1.0000
14.250 1.4650 0.08556 0.07813 -0.0881 0.0718 1.0000
14.500 1.4517 0.09098 0.08363 -0.0890 0.0684 1.0000
14.750 1.4403 0.09622 0.08900 -0.0900 0.0649 1.0000
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Polar data table (+)
Polar graphs
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