GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 777 AIRFOIL (goe777-il) Reynolds number: 100,000 Max Cl/Cd: 15.47 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe777-il-100000.txt Download as CSV file: xf-goe777-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 777 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1795 0.10894 0.10339 -0.0604 0.7063 0.1886
-10.750 -0.4347 0.06315 0.05675 -0.0895 0.7158 0.1087
-10.500 -0.4358 0.05959 0.05300 -0.0890 0.7125 0.1082
-10.250 -0.4423 0.05607 0.04925 -0.0881 0.7091 0.1080
-10.000 -0.4477 0.05284 0.04568 -0.0867 0.7056 0.1081
-9.750 -0.4497 0.04993 0.04236 -0.0850 0.7023 0.1083
-9.500 -0.4447 0.04732 0.03936 -0.0834 0.6991 0.1088
-9.250 -0.4238 0.04512 0.03715 -0.0831 0.6956 0.1102
-9.000 -0.4047 0.04368 0.03561 -0.0824 0.6924 0.1123
-8.750 -0.3894 0.04221 0.03395 -0.0815 0.6890 0.1147
-8.500 -0.3759 0.04067 0.03209 -0.0802 0.6857 0.1170
-8.250 -0.3622 0.03937 0.03032 -0.0787 0.6826 0.1192
-8.000 -0.3393 0.03782 0.02880 -0.0785 0.6796 0.1219
-7.750 -0.3162 0.03697 0.02792 -0.0781 0.6768 0.1258
-7.500 -0.2963 0.03612 0.02672 -0.0769 0.6740 0.1300
-7.250 -0.2725 0.03497 0.02550 -0.0764 0.6713 0.1340
-7.000 -0.2492 0.03445 0.02495 -0.0759 0.6685 0.1390
-6.750 -0.2288 0.03416 0.02447 -0.0753 0.6653 0.1441
-6.500 -0.2049 0.03358 0.02411 -0.0754 0.6624 0.1495
-6.250 -0.1830 0.03339 0.02383 -0.0748 0.6591 0.1558
-6.000 -0.1590 0.03285 0.02337 -0.0744 0.6558 0.1621
-5.750 -0.1347 0.03255 0.02303 -0.0738 0.6529 0.1697
-5.500 -0.1096 0.03209 0.02261 -0.0732 0.6504 0.1773
-5.250 -0.0849 0.03194 0.02240 -0.0725 0.6479 0.1863
-5.000 -0.0711 0.03236 0.02306 -0.0716 0.6428 0.1935
-4.750 -0.0542 0.03263 0.02339 -0.0705 0.6373 0.2030
-4.500 -0.0323 0.03228 0.02317 -0.0694 0.6328 0.2151
-4.250 -0.0068 0.03167 0.02264 -0.0683 0.6294 0.2332
-4.000 0.0176 0.03103 0.02220 -0.0670 0.6266 0.2664
-3.750 0.0175 0.03204 0.02369 -0.0647 0.6202 0.3133
-3.500 0.0200 0.03223 0.02458 -0.0618 0.6147 0.4220
-3.250 0.0343 0.03220 0.02512 -0.0589 0.6107 0.5386
-3.000 0.0597 0.03213 0.02510 -0.0569 0.6077 0.6068
-2.750 0.0898 0.03196 0.02488 -0.0552 0.6054 0.6527
-2.500 0.0693 0.03524 0.02840 -0.0521 0.5946 0.6699
-2.250 0.0895 0.03558 0.02877 -0.0500 0.5897 0.7017
-2.000 0.1196 0.03525 0.02836 -0.0483 0.5868 0.7346
-1.750 0.1534 0.03478 0.02784 -0.0466 0.5847 0.7646
-1.500 0.1159 0.03908 0.03241 -0.0426 0.5704 0.7777
-1.250 0.1431 0.03884 0.03214 -0.0400 0.5670 0.8092
-1.000 0.1777 0.03824 0.03147 -0.0378 0.5649 0.8392
-0.750 0.1364 0.04254 0.03598 -0.0335 0.5490 0.8561
-0.500 0.1764 0.04195 0.03530 -0.0324 0.5463 0.8854
-0.250 0.2269 0.04120 0.03440 -0.0328 0.5444 0.9121
0.000 0.2617 0.04289 0.03605 -0.0350 0.5373 0.9328
0.250 0.3754 0.04061 0.03341 -0.0436 0.5394 0.9440
0.500 0.3808 0.04436 0.03728 -0.0461 0.5248 0.9611
0.750 0.4066 0.04727 0.04020 -0.0504 0.5141 0.9754
1.000 0.5035 0.04391 0.03654 -0.0565 0.5172 0.9787
1.250 0.6037 0.04054 0.03279 -0.0638 0.5202 0.9808
1.500 0.6071 0.04531 0.03780 -0.0679 0.5041 0.9986
1.750 0.6429 0.04417 0.03651 -0.0684 0.5026 1.0000
2.000 0.6678 0.04316 0.03535 -0.0673 0.5013 1.0000
2.250 0.3108 0.06254 0.05515 -0.0387 0.4677 1.0000
2.500 0.3415 0.06260 0.05507 -0.0386 0.4654 1.0000
2.750 0.3783 0.06222 0.05455 -0.0386 0.4638 1.0000
3.000 0.3025 0.07180 0.06426 -0.0373 0.4561 1.0000
3.250 0.2979 0.07517 0.06759 -0.0370 0.4533 1.0000
3.500 0.3068 0.07740 0.06976 -0.0369 0.4507 1.0000
3.750 0.2755 0.08508 0.07754 -0.0381 0.4668 1.0000
4.000 0.2313 0.09327 0.08586 -0.0393 0.4953 1.0000
4.250 0.2391 0.09481 0.08735 -0.0389 0.4893 1.0000
4.500 0.2580 0.09662 0.08909 -0.0391 0.4863 1.0000
4.750 0.2812 0.09864 0.09103 -0.0394 0.4843 1.0000
5.000 0.3097 0.10098 0.09329 -0.0401 0.4828 1.0000
5.250 0.3431 0.10382 0.09605 -0.0411 0.4817 1.0000
5.500 0.3719 0.10718 0.09934 -0.0420 0.4810 1.0000
5.750 0.3035 0.10720 0.09945 -0.0388 0.4713 1.0000
6.000 0.3209 0.10907 0.10127 -0.0389 0.4680 1.0000
6.250 0.3428 0.11117 0.10332 -0.0393 0.4658 1.0000
6.500 0.3694 0.11369 0.10577 -0.0399 0.4643 1.0000
6.750 0.4024 0.11689 0.10892 -0.0409 0.4632 1.0000
7.000 0.3604 0.11792 0.10999 -0.0392 0.4568 1.0000
7.250 0.3714 0.11969 0.11174 -0.0393 0.4520 1.0000
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Polar data table (+)
Polar graphs
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