GOE 646 AIRFOIL (goe646-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 646 AIRFOIL (goe646-il) Reynolds number: 50,000 Max Cl/Cd: 18.51 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe646-il-50000-n5.txt Download as CSV file: xf-goe646-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 646 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3464 0.12477 0.11677 -0.0490 1.0000 0.1104
-11.750 -0.3630 0.12025 0.11231 -0.0494 1.0000 0.1116
-11.500 -0.3812 0.11562 0.10774 -0.0498 1.0000 0.1131
-11.250 -0.3770 0.11500 0.10718 -0.0477 1.0000 0.1148
-11.000 -0.3810 0.11310 0.10534 -0.0464 1.0000 0.1169
-10.750 -0.3936 0.10986 0.10215 -0.0459 1.0000 0.1188
-10.500 -0.4166 0.10500 0.09735 -0.0462 1.0000 0.1209
-10.250 -0.4812 0.09347 0.08592 -0.0501 1.0000 0.1239
-10.000 -0.4492 0.09526 0.08772 -0.0490 0.9970 0.1263
-9.750 -0.4405 0.09108 0.08350 -0.0531 0.9909 0.1303
-9.500 -0.6224 0.06086 0.05291 -0.0742 0.9721 0.1337
-9.250 -0.6382 0.05505 0.04678 -0.0781 0.9607 0.1373
-9.000 -0.6071 0.05465 0.04642 -0.0796 0.9543 0.1421
-8.750 -0.6137 0.05002 0.04136 -0.0816 0.9430 0.1472
-8.500 -0.5881 0.04888 0.04020 -0.0830 0.9360 0.1524
-8.250 -0.5719 0.04728 0.03847 -0.0835 0.9266 0.1582
-8.000 -0.5512 0.04525 0.03621 -0.0852 0.9191 0.1650
-7.750 -0.5303 0.04456 0.03551 -0.0850 0.9100 0.1708
-7.500 -0.5023 0.04275 0.03344 -0.0873 0.9041 0.1794
-7.250 -0.4858 0.04234 0.03307 -0.0860 0.8935 0.1851
-7.000 -0.4577 0.04085 0.03132 -0.0877 0.8870 0.1945
-6.750 -0.4370 0.04059 0.03111 -0.0869 0.8778 0.2013
-6.500 -0.4120 0.03949 0.02980 -0.0876 0.8700 0.2109
-6.250 -0.3763 0.03894 0.02919 -0.0894 0.8651 0.2216
-6.000 -0.3643 0.03855 0.02874 -0.0873 0.8534 0.2290
-5.750 -0.3328 0.03786 0.02788 -0.0885 0.8475 0.2409
-5.500 -0.3124 0.03781 0.02786 -0.0874 0.8384 0.2489
-5.250 -0.2876 0.03712 0.02693 -0.0877 0.8304 0.2611
-5.000 -0.2517 0.03702 0.02688 -0.0887 0.8258 0.2715
-4.750 -0.2401 0.03677 0.02647 -0.0867 0.8146 0.2812
-4.500 -0.2096 0.03662 0.02630 -0.0871 0.8087 0.2924
-4.250 -0.1730 0.03627 0.02587 -0.0885 0.8049 0.3049
-4.000 -0.1658 0.03633 0.02581 -0.0857 0.7926 0.3147
-3.750 -0.1329 0.03612 0.02560 -0.0863 0.7879 0.3259
-3.500 -0.1170 0.03599 0.02523 -0.0851 0.7789 0.3375
-3.250 -0.0930 0.03601 0.02535 -0.0843 0.7721 0.3457
-3.000 -0.0591 0.03549 0.02462 -0.0854 0.7681 0.3587
-2.750 -0.0478 0.03579 0.02498 -0.0830 0.7583 0.3652
-2.500 -0.0209 0.03554 0.02457 -0.0831 0.7523 0.3767
-2.250 0.0131 0.03518 0.02421 -0.0838 0.7487 0.3862
-2.000 0.0213 0.03564 0.02460 -0.0814 0.7391 0.3946
-1.750 0.0481 0.03551 0.02442 -0.0813 0.7335 0.4043
-1.500 0.0828 0.03515 0.02398 -0.0822 0.7300 0.4159
-1.250 0.0911 0.03572 0.02453 -0.0798 0.7206 0.4236
-1.000 0.1156 0.03576 0.02456 -0.0793 0.7150 0.4332
-0.750 0.1487 0.03546 0.02419 -0.0800 0.7115 0.4449
-0.500 0.1580 0.03615 0.02491 -0.0777 0.7028 0.4530
-0.250 0.1816 0.03630 0.02499 -0.0773 0.6967 0.4641
0.000 0.2149 0.03605 0.02476 -0.0777 0.6930 0.4759
0.500 0.2494 0.03702 0.02573 -0.0753 0.6781 0.4968
0.750 0.2844 0.03667 0.02537 -0.0759 0.6742 0.5109
1.250 0.3231 0.03734 0.02610 -0.0736 0.6582 0.5362
1.500 0.3622 0.03671 0.02548 -0.0744 0.6544 0.5543
2.000 0.3993 0.03744 0.02630 -0.0719 0.6378 0.5879
2.250 0.4393 0.03676 0.02566 -0.0727 0.6343 0.6129
2.750 0.4703 0.03777 0.02685 -0.0695 0.6174 0.6592
3.000 0.5110 0.03692 0.02609 -0.0702 0.6143 0.6962
3.500 0.5392 0.03780 0.02738 -0.0664 0.5969 0.7787
3.750 0.6038 0.03634 0.02618 -0.0709 0.5939 1.0000
4.250 0.6355 0.03795 0.02756 -0.0689 0.5756 1.0000
4.750 0.6671 0.03955 0.02900 -0.0666 0.5571 1.0000
5.000 0.7148 0.03861 0.02794 -0.0681 0.5540 1.0000
5.250 0.6985 0.04117 0.03052 -0.0642 0.5386 1.0000
5.500 0.7436 0.04023 0.02947 -0.0652 0.5350 1.0000
6.000 0.7713 0.04199 0.03117 -0.0624 0.5159 1.0000
6.500 0.7991 0.04377 0.03290 -0.0597 0.4969 1.0000
7.000 0.8248 0.04578 0.03489 -0.0570 0.4779 1.0000
7.500 0.8497 0.04787 0.03696 -0.0544 0.4592 1.0000
8.000 0.8733 0.05011 0.03920 -0.0519 0.4407 1.0000
8.500 0.8939 0.05273 0.04183 -0.0496 0.4227 1.0000
9.000 0.9109 0.05588 0.04502 -0.0474 0.4051 1.0000
9.500 0.9244 0.05960 0.04877 -0.0455 0.3880 1.0000
10.000 0.9324 0.06421 0.05346 -0.0440 0.3713 1.0000
10.250 0.9707 0.06269 0.05193 -0.0433 0.3687 1.0000
10.750 0.9675 0.06884 0.05817 -0.0421 0.3519 1.0000
11.250 0.9582 0.07623 0.06568 -0.0417 0.3349 1.0000
11.500 0.9777 0.07688 0.06635 -0.0410 0.3306 1.0000
12.000 0.9682 0.08490 0.07450 -0.0412 0.3154 1.0000
12.500 0.9393 0.09630 0.08603 -0.0430 0.2979 1.0000
12.750 0.9694 0.09526 0.08504 -0.0418 0.2961 1.0000
13.250 0.9309 0.10900 0.09893 -0.0451 0.2791 1.0000
13.500 0.8858 0.12011 0.11010 -0.0489 0.2674 1.0000
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Polar data table (+)
Polar graphs
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