GOE 336 (MVA H.44) AIRFOIL (goe336-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 336 (MVA H.44) AIRFOIL (goe336-il) Reynolds number: 200,000 Max Cl/Cd: 77.34 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe336-il-200000-n5.txt Download as CSV file: xf-goe336-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 336 (MVA H.44) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2079 0.08776 0.08467 -0.0368 0.9919 0.0284
-8.500 -0.1929 0.08419 0.08110 -0.0383 0.9792 0.0296
-8.250 -0.3067 0.09580 0.09258 -0.0331 1.0000 0.0274
-8.000 -0.2968 0.09183 0.08863 -0.0379 0.9891 0.0275
-7.750 -0.2827 0.08728 0.08409 -0.0363 0.9815 0.0286
-7.500 -0.2647 0.08377 0.08057 -0.0395 0.9637 0.0294
-7.250 -0.2465 0.08008 0.07685 -0.0439 0.9414 0.0304
-7.000 -0.2270 0.07619 0.07290 -0.0488 0.9171 0.0317
-6.750 -0.1978 0.07176 0.06826 -0.0616 0.8856 0.0361
-6.500 -0.1785 0.06775 0.06409 -0.0651 0.8587 0.0363
-6.250 -0.1610 0.06378 0.05995 -0.0674 0.8330 0.0363
-6.000 -0.1442 0.05991 0.05589 -0.0691 0.8100 0.0363
-5.750 -0.1383 0.05703 0.05297 -0.0667 0.7896 0.0345
-5.250 -0.0938 0.04907 0.04452 -0.0721 0.7585 0.0355
-5.000 -0.0741 0.04583 0.04108 -0.0730 0.7458 0.0350
-4.250 -0.0027 0.03487 0.02920 -0.0758 0.7150 0.0362
-4.000 0.0194 0.03156 0.02557 -0.0758 0.7056 0.0360
-3.750 0.0423 0.02807 0.02170 -0.0755 0.6966 0.0361
-3.250 0.0880 0.02235 0.01510 -0.0745 0.6780 0.0374
-3.000 0.1129 0.02034 0.01264 -0.0738 0.6686 0.0374
-2.750 0.1384 0.01891 0.01085 -0.0733 0.6588 0.0377
-2.500 0.1647 0.01781 0.00948 -0.0729 0.6489 0.0381
-2.250 0.1912 0.01697 0.00839 -0.0725 0.6395 0.0386
-2.000 0.2179 0.01627 0.00750 -0.0722 0.6295 0.0392
-1.750 0.2448 0.01569 0.00677 -0.0719 0.6198 0.0399
-1.500 0.2715 0.01530 0.00625 -0.0715 0.6105 0.0414
-1.250 0.2984 0.01490 0.00574 -0.0712 0.6005 0.0427
-1.000 0.3251 0.01450 0.00523 -0.0709 0.5913 0.0433
-0.750 0.3516 0.01416 0.00478 -0.0705 0.5823 0.0439
-0.500 0.3781 0.01389 0.00444 -0.0701 0.5739 0.0447
-0.250 0.4045 0.01369 0.00416 -0.0697 0.5664 0.0457
0.250 0.4574 0.01339 0.00378 -0.0689 0.5525 0.0498
0.500 0.4840 0.01330 0.00370 -0.0686 0.5464 0.0543
0.750 0.5106 0.01324 0.00367 -0.0683 0.5404 0.0653
1.000 0.5371 0.01325 0.00368 -0.0680 0.5353 0.0874
1.250 0.5639 0.01325 0.00372 -0.0678 0.5297 0.1085
1.500 0.5904 0.01327 0.00374 -0.0676 0.5241 0.1218
1.750 0.6167 0.01331 0.00374 -0.0672 0.5191 0.1333
2.000 0.6431 0.01330 0.00381 -0.0670 0.5132 0.1539
2.250 0.6691 0.01330 0.00388 -0.0667 0.5077 0.1861
2.750 0.7813 0.01207 0.00426 -0.0794 0.4931 1.0000
3.000 0.8062 0.01224 0.00433 -0.0788 0.4875 1.0000
3.250 0.8312 0.01237 0.00444 -0.0782 0.4802 1.0000
3.500 0.8556 0.01255 0.00453 -0.0776 0.4729 1.0000
3.750 0.8802 0.01267 0.00465 -0.0769 0.4639 1.0000
4.000 0.9044 0.01284 0.00476 -0.0762 0.4561 1.0000
4.250 0.9291 0.01298 0.00493 -0.0756 0.4488 1.0000
4.500 0.9531 0.01317 0.00506 -0.0749 0.4419 1.0000
4.750 0.9775 0.01331 0.00525 -0.0743 0.4332 1.0000
5.000 1.0012 0.01350 0.00542 -0.0735 0.4250 1.0000
5.250 1.0251 0.01366 0.00561 -0.0728 0.4152 1.0000
5.500 1.0487 0.01385 0.00582 -0.0721 0.4057 1.0000
5.750 1.0719 0.01405 0.00602 -0.0712 0.3962 1.0000
6.000 1.0954 0.01424 0.00628 -0.0705 0.3849 1.0000
6.250 1.1183 0.01446 0.00653 -0.0697 0.3718 1.0000
6.500 1.1389 0.01476 0.00676 -0.0684 0.3413 1.0000
6.750 1.1496 0.01570 0.00722 -0.0658 0.2607 1.0000
7.000 1.1604 0.01682 0.00802 -0.0633 0.2150 1.0000
7.250 1.1758 0.01760 0.00867 -0.0615 0.1887 1.0000
7.500 1.1908 0.01837 0.00932 -0.0596 0.1580 1.0000
7.750 1.2037 0.01925 0.01003 -0.0575 0.1304 1.0000
8.000 1.2168 0.02008 0.01078 -0.0554 0.1114 1.0000
8.250 1.2297 0.02090 0.01153 -0.0533 0.0906 1.0000
8.500 1.2345 0.02218 0.01256 -0.0502 0.0622 1.0000
8.750 1.2441 0.02307 0.01342 -0.0476 0.0552 1.0000
9.000 1.2546 0.02379 0.01420 -0.0451 0.0495 1.0000
9.250 1.2622 0.02472 0.01514 -0.0424 0.0435 1.0000
9.500 1.2741 0.02546 0.01597 -0.0405 0.0241 1.0000
9.750 1.2734 0.02710 0.01751 -0.0373 0.0191 1.0000
10.000 1.2792 0.02844 0.01892 -0.0352 0.0173 1.0000
10.250 1.2860 0.02980 0.02040 -0.0334 0.0162 1.0000
10.500 1.2916 0.03136 0.02210 -0.0317 0.0152 1.0000
10.750 1.2958 0.03316 0.02404 -0.0303 0.0144 1.0000
11.000 1.2989 0.03517 0.02619 -0.0290 0.0139 1.0000
11.250 1.3011 0.03739 0.02856 -0.0280 0.0134 1.0000
11.500 1.3016 0.03987 0.03121 -0.0271 0.0130 1.0000
11.750 1.3005 0.04261 0.03411 -0.0263 0.0127 1.0000
12.000 1.3021 0.04511 0.03674 -0.0258 0.0125 1.0000
12.250 1.3032 0.04773 0.03949 -0.0254 0.0123 1.0000
12.500 1.3033 0.05052 0.04241 -0.0250 0.0121 1.0000
12.750 1.3020 0.05349 0.04553 -0.0248 0.0118 1.0000
13.000 1.2998 0.05665 0.04882 -0.0247 0.0114 1.0000
13.250 1.2965 0.06001 0.05231 -0.0248 0.0111 1.0000
13.500 1.2923 0.06357 0.05599 -0.0250 0.0108 1.0000
13.750 1.2874 0.06731 0.05985 -0.0253 0.0105 1.0000
14.000 1.2818 0.07125 0.06391 -0.0258 0.0103 1.0000
14.250 1.2760 0.07528 0.06805 -0.0264 0.0102 1.0000
14.500 1.2699 0.07943 0.07232 -0.0271 0.0100 1.0000
14.750 1.2640 0.08361 0.07660 -0.0278 0.0099 1.0000
15.000 1.2582 0.08781 0.08088 -0.0286 0.0098 1.0000
15.250 1.2528 0.09191 0.08505 -0.0294 0.0097 1.0000
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Polar data table (+)
Polar graphs
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