GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 647 AIRFOIL (goe647-il) Reynolds number: 50,000 Max Cl/Cd: 28.3 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe647-il-50000-n5.txt Download as CSV file: xf-goe647-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 647 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2622 0.11632 0.10957 -0.0434 1.0000 0.0866
-10.250 -0.2689 0.11416 0.10751 -0.0420 1.0000 0.0865
-10.000 -0.2766 0.11220 0.10564 -0.0403 1.0000 0.0862
-9.750 -0.2861 0.11038 0.10392 -0.0385 1.0000 0.0859
-9.500 -0.2960 0.10853 0.10217 -0.0368 0.9998 0.0854
-9.250 -0.2803 0.10369 0.09732 -0.0419 0.9918 0.0845
-9.000 -0.2686 0.09867 0.09230 -0.0472 0.9831 0.0837
-8.750 -0.2607 0.09358 0.08721 -0.0524 0.9731 0.0832
-8.500 -0.2577 0.08821 0.08184 -0.0580 0.9619 0.0834
-8.250 -0.2595 0.08251 0.07614 -0.0639 0.9496 0.0835
-8.000 -0.2681 0.07552 0.06911 -0.0712 0.9356 0.0834
-7.750 -0.2825 0.06598 0.05936 -0.0805 0.9210 0.0830
-7.500 -0.2916 0.05885 0.05187 -0.0858 0.9076 0.0829
-7.250 -0.2935 0.05387 0.04648 -0.0877 0.8941 0.0832
-7.000 -0.2824 0.04943 0.04154 -0.0899 0.8842 0.0839
-6.750 -0.2681 0.04588 0.03745 -0.0909 0.8738 0.0852
-6.500 -0.2506 0.04313 0.03417 -0.0913 0.8639 0.0871
-6.250 -0.2220 0.04158 0.03257 -0.0922 0.8555 0.0898
-6.000 -0.1975 0.03991 0.03066 -0.0924 0.8464 0.0923
-5.750 -0.1717 0.03813 0.02854 -0.0926 0.8372 0.0948
-5.500 -0.1454 0.03651 0.02650 -0.0927 0.8284 0.0977
-5.250 -0.1187 0.03533 0.02529 -0.0926 0.8189 0.1015
-5.000 -0.0907 0.03425 0.02407 -0.0926 0.8100 0.1064
-4.750 -0.0631 0.03311 0.02264 -0.0924 0.8002 0.1119
-4.500 -0.0367 0.03217 0.02177 -0.0920 0.7905 0.1178
-4.250 -0.0074 0.03119 0.02065 -0.0919 0.7809 0.1272
-4.000 0.0169 0.03048 0.01995 -0.0911 0.7697 0.1380
-3.750 0.0503 0.02956 0.01906 -0.0916 0.7609 0.1557
-3.500 0.0721 0.02916 0.01875 -0.0904 0.7483 0.1762
-3.250 0.1083 0.02839 0.01799 -0.0912 0.7401 0.2144
-3.000 0.1288 0.02816 0.01782 -0.0897 0.7271 0.2496
-2.750 0.1532 0.02790 0.01758 -0.0887 0.7158 0.2881
-2.500 0.1831 0.02754 0.01719 -0.0884 0.7062 0.3266
-2.250 0.2041 0.02750 0.01709 -0.0869 0.6937 0.3562
-2.000 0.2345 0.02716 0.01671 -0.0866 0.6842 0.3846
-1.750 0.2586 0.02705 0.01651 -0.0855 0.6723 0.4113
-1.500 0.2820 0.02693 0.01641 -0.0843 0.6606 0.4408
-1.250 0.3136 0.02654 0.01593 -0.0841 0.6511 0.4735
-1.000 0.3351 0.02645 0.01586 -0.0827 0.6382 0.4993
-0.750 0.3633 0.02615 0.01551 -0.0823 0.6273 0.5272
-0.500 0.3909 0.02582 0.01520 -0.0817 0.6161 0.5580
-0.250 0.4128 0.02567 0.01518 -0.0803 0.6037 0.5955
0.000 0.4418 0.02522 0.01487 -0.0796 0.5936 0.6568
0.250 0.4817 0.02478 0.01488 -0.0808 0.5803 0.7965
0.500 0.5471 0.02482 0.01470 -0.0879 0.5651 1.0000
0.750 0.5705 0.02504 0.01463 -0.0871 0.5541 1.0000
1.000 0.5936 0.02528 0.01461 -0.0862 0.5430 1.0000
1.250 0.6126 0.02568 0.01482 -0.0847 0.5313 1.0000
1.500 0.6395 0.02584 0.01469 -0.0842 0.5218 1.0000
1.750 0.6565 0.02633 0.01506 -0.0825 0.5103 1.0000
2.000 0.6798 0.02666 0.01518 -0.0817 0.5009 1.0000
2.250 0.7005 0.02708 0.01544 -0.0804 0.4910 1.0000
2.500 0.7219 0.02751 0.01571 -0.0794 0.4820 1.0000
2.750 0.7434 0.02793 0.01599 -0.0783 0.4732 1.0000
3.000 0.7650 0.02841 0.01632 -0.0773 0.4651 1.0000
3.250 0.7848 0.02895 0.01676 -0.0761 0.4569 1.0000
3.500 0.8101 0.02932 0.01696 -0.0756 0.4502 1.0000
3.750 0.8251 0.03007 0.01769 -0.0738 0.4420 1.0000
4.000 0.8512 0.03044 0.01789 -0.0734 0.4359 1.0000
4.250 0.8669 0.03124 0.01867 -0.0719 0.4290 1.0000
4.500 0.8857 0.03193 0.01930 -0.0707 0.4226 1.0000
4.750 0.9137 0.03229 0.01950 -0.0706 0.4177 1.0000
5.000 0.9241 0.03335 0.02061 -0.0684 0.4113 1.0000
5.250 0.9410 0.03414 0.02138 -0.0671 0.4055 1.0000
5.500 0.9679 0.03457 0.02169 -0.0669 0.4010 1.0000
5.750 0.9793 0.03567 0.02282 -0.0650 0.3958 1.0000
6.000 0.9880 0.03689 0.02409 -0.0628 0.3906 1.0000
6.250 1.0075 0.03768 0.02486 -0.0619 0.3864 1.0000
6.500 1.0372 0.03810 0.02517 -0.0622 0.3829 1.0000
6.750 1.0318 0.03989 0.02710 -0.0585 0.3781 1.0000
7.000 1.0282 0.04165 0.02896 -0.0552 0.3733 1.0000
7.250 1.0430 0.04268 0.02998 -0.0539 0.3693 1.0000
7.500 1.0727 0.04308 0.03031 -0.0541 0.3662 1.0000
7.750 1.0625 0.04544 0.03278 -0.0507 0.3622 1.0000
8.000 1.0091 0.05090 0.03851 -0.0453 0.3564 1.0000
8.250 1.0022 0.05387 0.04154 -0.0437 0.3522 1.0000
8.500 1.0250 0.05455 0.04220 -0.0432 0.3496 1.0000
8.750 1.0659 0.05391 0.04150 -0.0435 0.3477 1.0000
9.000 0.8918 0.07487 0.06290 -0.0424 0.3321 1.0000
9.250 0.9148 0.07532 0.06333 -0.0417 0.3305 1.0000
10.750 0.8023 0.11390 0.10232 -0.0499 0.2994 1.0000
11.000 0.8208 0.11517 0.10360 -0.0496 0.2973 1.0000
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Polar data table (+)
Polar graphs
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