GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 200,000 Max Cl/Cd: 79.69 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe264-il-200000-n5.txt Download as CSV file: xf-goe264-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 264 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3031 0.09415 0.09086 -0.0249 1.0000 0.0175
-7.500 -0.3075 0.09216 0.08894 -0.0236 1.0000 0.0174
-7.250 -0.3113 0.09006 0.08689 -0.0228 1.0000 0.0174
-7.000 -0.2951 0.08589 0.08273 -0.0278 0.9954 0.0174
-6.750 -0.2666 0.07941 0.07623 -0.0393 0.9881 0.0181
-6.500 -0.2441 0.07780 0.07462 -0.0406 0.9846 0.0199
-6.250 -0.2161 0.07364 0.07041 -0.0474 0.9781 0.0208
-6.000 -0.1863 0.06884 0.06556 -0.0549 0.9707 0.0211
-5.750 -0.1522 0.06391 0.06055 -0.0632 0.9643 0.0218
-5.500 -0.1137 0.05794 0.05446 -0.0735 0.9546 0.0244
-5.250 -0.0782 0.05292 0.04932 -0.0810 0.9460 0.0258
-5.000 -0.0503 0.05072 0.04706 -0.0836 0.9376 0.0271
-4.750 -0.0182 0.04762 0.04383 -0.0880 0.9270 0.0302
-4.500 0.0327 0.04023 0.03607 -0.0984 0.9183 0.0332
-4.250 0.0533 0.03994 0.03576 -0.0978 0.9071 0.0349
-4.000 0.0829 0.03793 0.03362 -0.0998 0.8947 0.0382
-3.750 0.1196 0.03416 0.02956 -0.1037 0.8826 0.0394
-3.500 0.1624 0.02914 0.02406 -0.1083 0.8708 0.0426
-3.250 0.1932 0.02640 0.02102 -0.1100 0.8567 0.0433
-3.000 0.2225 0.02458 0.01897 -0.1109 0.8414 0.0441
-2.750 0.2524 0.02280 0.01690 -0.1117 0.8249 0.0449
-2.500 0.2818 0.02132 0.01514 -0.1122 0.8076 0.0461
-2.250 0.3115 0.01998 0.01350 -0.1127 0.7886 0.0481
-2.000 0.3432 0.01779 0.01082 -0.1136 0.7683 0.0483
-1.750 0.3732 0.01631 0.00890 -0.1139 0.7462 0.0488
-1.500 0.4020 0.01534 0.00755 -0.1139 0.7210 0.0498
-1.250 0.4301 0.01468 0.00654 -0.1138 0.6952 0.0511
-1.000 0.4579 0.01422 0.00580 -0.1136 0.6720 0.0524
-0.750 0.4855 0.01392 0.00525 -0.1134 0.6516 0.0536
-0.500 0.5132 0.01363 0.00475 -0.1133 0.6338 0.0547
-0.250 0.5409 0.01328 0.00431 -0.1134 0.6180 0.0578
0.000 0.5685 0.01319 0.00414 -0.1133 0.6032 0.0610
0.250 0.5964 0.01305 0.00391 -0.1133 0.5892 0.0635
0.500 0.6244 0.01294 0.00372 -0.1133 0.5756 0.0659
0.750 0.6523 0.01287 0.00357 -0.1133 0.5621 0.0683
1.000 0.6803 0.01279 0.00349 -0.1134 0.5485 0.0730
1.250 0.7081 0.01279 0.00346 -0.1134 0.5353 0.0792
1.500 0.7358 0.01281 0.00350 -0.1134 0.5221 0.0921
1.750 0.7635 0.01284 0.00357 -0.1134 0.5087 0.1143
2.000 0.7909 0.01292 0.00364 -0.1134 0.4955 0.1410
2.250 0.8182 0.01300 0.00373 -0.1133 0.4829 0.1646
2.500 0.8456 0.01308 0.00386 -0.1133 0.4711 0.1973
2.750 0.8731 0.01304 0.00403 -0.1135 0.4598 0.2993
3.250 0.9188 0.01221 0.00423 -0.1113 0.4393 1.0000
3.500 0.9459 0.01244 0.00440 -0.1112 0.4286 1.0000
3.750 0.9728 0.01269 0.00459 -0.1110 0.4188 1.0000
4.000 0.9995 0.01296 0.00482 -0.1109 0.4093 1.0000
4.250 1.0265 0.01320 0.00506 -0.1108 0.4005 1.0000
4.500 1.0530 0.01349 0.00531 -0.1107 0.3929 1.0000
4.750 1.0799 0.01373 0.00559 -0.1105 0.3854 1.0000
5.000 1.1062 0.01404 0.00590 -0.1104 0.3782 1.0000
5.250 1.1328 0.01429 0.00622 -0.1102 0.3704 1.0000
5.500 1.1588 0.01462 0.00655 -0.1100 0.3641 1.0000
5.750 1.1852 0.01488 0.00692 -0.1098 0.3561 1.0000
6.000 1.2105 0.01519 0.00724 -0.1095 0.3411 1.0000
6.250 1.2349 0.01555 0.00756 -0.1091 0.3214 1.0000
6.500 1.2591 0.01593 0.00792 -0.1086 0.2963 1.0000
6.750 1.2827 0.01640 0.00834 -0.1081 0.2685 1.0000
7.000 1.3031 0.01725 0.00895 -0.1072 0.2096 1.0000
7.250 1.3073 0.02029 0.01095 -0.1047 0.0540 1.0000
7.500 1.3238 0.02162 0.01221 -0.1032 0.0302 1.0000
7.750 1.3425 0.02259 0.01326 -0.1019 0.0232 1.0000
8.000 1.3591 0.02371 0.01449 -0.1004 0.0196 1.0000
8.250 1.3736 0.02496 0.01591 -0.0985 0.0178 1.0000
8.500 1.3887 0.02603 0.01718 -0.0968 0.0163 1.0000
8.750 1.4016 0.02720 0.01848 -0.0948 0.0149 1.0000
9.000 1.4108 0.02855 0.01998 -0.0924 0.0140 1.0000
9.250 1.4159 0.03002 0.02157 -0.0894 0.0133 1.0000
9.500 1.4162 0.03168 0.02335 -0.0858 0.0128 1.0000
9.750 1.4148 0.03367 0.02547 -0.0826 0.0124 1.0000
10.000 1.4110 0.03607 0.02799 -0.0796 0.0120 1.0000
10.250 1.4043 0.03901 0.03105 -0.0767 0.0115 1.0000
10.500 1.4066 0.04125 0.03341 -0.0749 0.0111 1.0000
10.750 1.4111 0.04336 0.03566 -0.0734 0.0107 1.0000
11.000 1.4145 0.04567 0.03811 -0.0721 0.0102 1.0000
11.250 1.4169 0.04820 0.04077 -0.0707 0.0099 1.0000
11.500 1.4192 0.05083 0.04358 -0.0694 0.0096 1.0000
11.750 1.4217 0.05351 0.04640 -0.0682 0.0094 1.0000
12.000 1.4240 0.05628 0.04931 -0.0670 0.0091 1.0000
12.250 1.4258 0.05917 0.05236 -0.0661 0.0089 1.0000
12.500 1.4269 0.06221 0.05556 -0.0652 0.0088 1.0000
12.750 1.4269 0.06543 0.05895 -0.0646 0.0086 1.0000
13.000 1.4255 0.06889 0.06257 -0.0641 0.0085 1.0000
13.250 1.4229 0.07259 0.06646 -0.0639 0.0083 1.0000
13.500 1.4187 0.07651 0.07055 -0.0640 0.0082 1.0000
13.750 1.4134 0.08063 0.07483 -0.0644 0.0081 1.0000
14.000 1.4070 0.08500 0.07936 -0.0651 0.0080 1.0000
14.250 1.3992 0.08970 0.08422 -0.0660 0.0078 1.0000
14.500 1.3893 0.09487 0.08956 -0.0671 0.0077 1.0000
14.750 1.3767 0.10072 0.09559 -0.0688 0.0076 1.0000
15.000 1.3648 0.10672 0.10183 -0.0715 0.0075 1.0000
15.250 1.3523 0.11306 0.10839 -0.0745 0.0075 1.0000
15.500 1.3393 0.11979 0.11534 -0.0780 0.0075 1.0000
15.750 1.3261 0.12685 0.12260 -0.0818 0.0074 1.0000
16.000 1.3128 0.13427 0.13022 -0.0861 0.0074 1.0000
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Polar data table (+)
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