Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 2 (glennmartin2-il) Reynolds number: 50,000 Max Cl/Cd: 31.65 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin2-il-50000-n5.txt Download as CSV file: xf-glennmartin2-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 2
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2858 0.11453 0.10896 -0.0286 0.9909 0.1099
-8.500 -0.2912 0.11214 0.10662 -0.0349 0.9815 0.1117
-8.250 -0.2942 0.10921 0.10373 -0.0395 0.9717 0.1122
-7.750 -0.2818 0.09362 0.08798 -0.0501 0.9539 0.0664
-7.500 -0.2707 0.08950 0.08383 -0.0525 0.9455 0.0661
-7.250 -0.2545 0.08695 0.08132 -0.0525 0.9384 0.0698
-7.000 -0.2465 0.08327 0.07759 -0.0546 0.9287 0.0704
-6.750 -0.2327 0.07895 0.07317 -0.0581 0.9207 0.0709
-6.500 -0.2272 0.07488 0.06900 -0.0596 0.9094 0.0705
-6.250 -0.2140 0.07031 0.06426 -0.0621 0.9001 0.0703
-6.000 -0.1967 0.06675 0.06053 -0.0639 0.8905 0.0729
-5.750 -0.1847 0.06305 0.05662 -0.0645 0.8791 0.0751
-5.500 -0.1643 0.05823 0.05144 -0.0664 0.8701 0.0762
-5.250 -0.1481 0.05367 0.04644 -0.0668 0.8593 0.0775
-5.000 -0.1354 0.04918 0.04119 -0.0659 0.8474 0.0805
-4.750 -0.1097 0.04695 0.03891 -0.0660 0.8367 0.0836
-4.500 -0.0822 0.04408 0.03564 -0.0661 0.8268 0.0859
-4.250 -0.0633 0.04199 0.03319 -0.0646 0.8143 0.0897
-4.000 -0.0395 0.03946 0.02998 -0.0637 0.8044 0.0949
-3.750 -0.0108 0.03721 0.02728 -0.0635 0.7962 0.0981
-3.500 0.0105 0.03601 0.02590 -0.0622 0.7853 0.1017
-3.250 0.0480 0.03431 0.02376 -0.0632 0.7788 0.1107
-3.000 0.0702 0.03331 0.02263 -0.0620 0.7668 0.1165
-2.750 0.1008 0.03221 0.02130 -0.0619 0.7565 0.1246
-2.500 0.1419 0.03107 0.02004 -0.0636 0.7481 0.1377
-2.250 0.1741 0.03044 0.01932 -0.0640 0.7356 0.1506
-2.000 0.2088 0.02982 0.01860 -0.0647 0.7236 0.1665
-1.750 0.2462 0.02914 0.01779 -0.0656 0.7120 0.1869
-1.500 0.2882 0.02832 0.01689 -0.0673 0.7008 0.2098
-1.250 0.3215 0.02776 0.01624 -0.0676 0.6865 0.2402
-1.000 0.3570 0.02707 0.01546 -0.0683 0.6719 0.2771
-0.750 0.3926 0.02635 0.01466 -0.0692 0.6564 0.3202
-0.500 0.4265 0.02567 0.01396 -0.0698 0.6401 0.3609
-0.250 0.5850 0.02377 0.01337 -0.0950 0.6116 1.0000
0.000 0.6099 0.02395 0.01320 -0.0942 0.5927 1.0000
0.250 0.6321 0.02420 0.01313 -0.0929 0.5740 1.0000
0.500 0.6524 0.02449 0.01314 -0.0914 0.5565 1.0000
0.750 0.6703 0.02483 0.01325 -0.0895 0.5396 1.0000
1.000 0.6897 0.02515 0.01334 -0.0879 0.5249 1.0000
1.250 0.7085 0.02551 0.01350 -0.0863 0.5119 1.0000
1.500 0.7283 0.02588 0.01369 -0.0849 0.5006 1.0000
1.750 0.7503 0.02622 0.01381 -0.0839 0.4916 1.0000
2.000 0.7715 0.02661 0.01402 -0.0828 0.4827 1.0000
2.250 0.7934 0.02701 0.01424 -0.0819 0.4750 1.0000
2.500 0.8156 0.02742 0.01450 -0.0810 0.4677 1.0000
2.750 0.8395 0.02784 0.01476 -0.0805 0.4613 1.0000
3.000 0.8607 0.02835 0.01519 -0.0796 0.4549 1.0000
3.250 0.8875 0.02876 0.01547 -0.0796 0.4498 1.0000
3.500 0.9100 0.02933 0.01598 -0.0789 0.4449 1.0000
3.750 0.9309 0.02994 0.01656 -0.0781 0.4400 1.0000
4.000 0.9562 0.03046 0.01701 -0.0779 0.4354 1.0000
4.250 0.9819 0.03102 0.01748 -0.0779 0.4313 1.0000
4.500 0.9974 0.03179 0.01831 -0.0762 0.4266 1.0000
4.750 1.0176 0.03248 0.01900 -0.0753 0.4223 1.0000
5.000 1.0432 0.03309 0.01958 -0.0753 0.4187 1.0000
5.250 1.0677 0.03380 0.02026 -0.0751 0.4155 1.0000
5.500 1.0776 0.03482 0.02142 -0.0727 0.4118 1.0000
5.750 1.0916 0.03575 0.02245 -0.0709 0.4080 1.0000
6.000 1.1119 0.03655 0.02326 -0.0702 0.4043 1.0000
6.250 1.1397 0.03721 0.02389 -0.0706 0.4010 1.0000
6.500 1.1462 0.03841 0.02523 -0.0678 0.3976 1.0000
6.750 1.1474 0.03979 0.02679 -0.0642 0.3940 1.0000
7.000 1.1563 0.04098 0.02808 -0.0619 0.3902 1.0000
7.250 1.1785 0.04175 0.02887 -0.0615 0.3865 1.0000
7.500 1.1993 0.04260 0.02974 -0.0609 0.3826 1.0000
7.750 1.1743 0.04469 0.03206 -0.0538 0.3784 1.0000
8.000 1.1675 0.04634 0.03382 -0.0496 0.3738 1.0000
8.250 1.1942 0.04684 0.03436 -0.0498 0.3694 1.0000
8.500 1.2015 0.04814 0.03573 -0.0476 0.3654 1.0000
8.750 1.1406 0.05275 0.04060 -0.0387 0.3605 1.0000
9.000 1.1222 0.05587 0.04384 -0.0352 0.3555 1.0000
9.250 1.1632 0.05524 0.04324 -0.0361 0.3520 1.0000
9.500 0.9759 0.07496 0.06320 -0.0288 0.3377 1.0000
9.750 1.0094 0.07380 0.06210 -0.0280 0.3355 1.0000
10.000 1.0509 0.07191 0.06027 -0.0272 0.3338 1.0000
10.500 0.8958 0.09867 0.08719 -0.0301 0.3051 1.0000
10.750 0.9154 0.09919 0.08777 -0.0294 0.3023 1.0000
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Polar data table (+)
Polar graphs
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