GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 428 AIRFOIL (goe428-il) Reynolds number: 200,000 Max Cl/Cd: 77.28 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe428-il-200000.txt Download as CSV file: xf-goe428-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 428 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3109 0.08827 0.08526 -0.0234 1.0000 0.0325
-6.750 -0.3270 0.08742 0.08451 -0.0202 1.0000 0.0328
-6.500 -0.3357 0.08599 0.08315 -0.0191 0.9991 0.0332
-6.250 -0.2949 0.08070 0.07782 -0.0333 0.9913 0.0355
-6.000 -0.2410 0.07527 0.07226 -0.0515 0.9838 0.0365
-5.750 -0.2081 0.06901 0.06594 -0.0605 0.9759 0.0369
-5.500 -0.1934 0.06369 0.06063 -0.0609 0.9719 0.0385
-5.250 -0.1664 0.06010 0.05702 -0.0645 0.9652 0.0402
-5.000 -0.1289 0.05582 0.05265 -0.0715 0.9592 0.0440
-4.750 -0.0729 0.04868 0.04515 -0.0858 0.9514 0.0502
-4.500 -0.0446 0.04568 0.04219 -0.0878 0.9458 0.0531
-4.250 0.0143 0.04065 0.03654 -0.0980 0.9390 0.0628
-4.000 0.0423 0.03684 0.03287 -0.1000 0.9310 0.0657
-3.750 0.0817 0.03343 0.02899 -0.1039 0.9207 0.0770
-3.500 0.1138 0.03109 0.02671 -0.1057 0.9142 0.0844
-3.250 0.1429 0.02879 0.02420 -0.1068 0.9029 0.0962
-3.000 0.1737 0.02639 0.02151 -0.1080 0.8921 0.1075
-2.750 0.2149 0.01748 0.01087 -0.1078 0.8847 0.0511
-2.500 0.2442 0.01634 0.00954 -0.1078 0.8734 0.0556
-2.250 0.2730 0.01502 0.00789 -0.1074 0.8615 0.0574
-2.000 0.3017 0.01437 0.00698 -0.1070 0.8495 0.0619
-1.750 0.3290 0.01326 0.00579 -0.1065 0.8380 0.0662
-1.500 0.3564 0.01277 0.00519 -0.1060 0.8261 0.0718
-1.250 0.3832 0.01230 0.00466 -0.1054 0.8142 0.0797
-1.000 0.4094 0.01198 0.00428 -0.1047 0.8016 0.0897
-0.750 0.4351 0.01167 0.00407 -0.1040 0.7889 0.1198
-0.500 0.4603 0.01126 0.00382 -0.1034 0.7765 0.1930
-0.250 0.4853 0.01094 0.00371 -0.1028 0.7642 0.2657
0.000 0.5279 0.00920 0.00361 -0.1057 0.7519 1.0000
0.250 0.5534 0.00929 0.00349 -0.1049 0.7387 1.0000
0.500 0.5789 0.00938 0.00340 -0.1042 0.7249 1.0000
0.750 0.6043 0.00947 0.00334 -0.1034 0.7108 1.0000
1.000 0.6297 0.00957 0.00330 -0.1027 0.6963 1.0000
1.250 0.6550 0.00968 0.00328 -0.1020 0.6812 1.0000
1.500 0.6802 0.00981 0.00328 -0.1012 0.6654 1.0000
1.750 0.7052 0.00996 0.00330 -0.1005 0.6488 1.0000
2.000 0.7301 0.01013 0.00334 -0.0997 0.6315 1.0000
2.250 0.7548 0.01032 0.00341 -0.0989 0.6131 1.0000
2.500 0.7792 0.01052 0.00351 -0.0981 0.5930 1.0000
2.750 0.8034 0.01074 0.00360 -0.0973 0.5731 1.0000
3.000 0.8275 0.01096 0.00372 -0.0964 0.5519 1.0000
3.250 0.8517 0.01121 0.00388 -0.0956 0.5323 1.0000
3.500 0.8758 0.01148 0.00403 -0.0949 0.5150 1.0000
3.750 0.9003 0.01176 0.00423 -0.0942 0.4992 1.0000
4.000 0.9248 0.01205 0.00445 -0.0936 0.4852 1.0000
4.250 0.9495 0.01237 0.00472 -0.0930 0.4729 1.0000
4.500 0.9742 0.01267 0.00501 -0.0924 0.4612 1.0000
4.750 0.9990 0.01298 0.00531 -0.0919 0.4505 1.0000
5.000 1.0238 0.01332 0.00562 -0.0914 0.4411 1.0000
5.250 1.0485 0.01365 0.00597 -0.0908 0.4317 1.0000
5.500 1.0734 0.01396 0.00634 -0.0903 0.4230 1.0000
5.750 1.0974 0.01430 0.00667 -0.0897 0.4126 1.0000
6.000 1.1195 0.01454 0.00693 -0.0887 0.3964 1.0000
6.250 1.1415 0.01479 0.00721 -0.0877 0.3806 1.0000
6.500 1.1630 0.01505 0.00752 -0.0866 0.3633 1.0000
6.750 1.1846 0.01533 0.00784 -0.0855 0.3470 1.0000
7.000 1.2050 0.01560 0.00816 -0.0842 0.3240 1.0000
7.250 1.2221 0.01600 0.00845 -0.0824 0.2762 1.0000
7.500 1.2258 0.01779 0.00941 -0.0790 0.1443 1.0000
7.750 1.2256 0.02020 0.01117 -0.0752 0.0468 1.0000
8.000 1.2362 0.02152 0.01243 -0.0726 0.0358 1.0000
8.250 1.2476 0.02269 0.01376 -0.0700 0.0319 1.0000
8.500 1.2577 0.02381 0.01507 -0.0673 0.0302 1.0000
8.750 1.2626 0.02505 0.01646 -0.0639 0.0289 1.0000
9.000 1.2654 0.02641 0.01795 -0.0603 0.0281 1.0000
9.250 1.2656 0.02800 0.01966 -0.0568 0.0271 1.0000
9.500 1.2649 0.02980 0.02154 -0.0536 0.0262 1.0000
9.750 1.2620 0.03199 0.02382 -0.0506 0.0251 1.0000
10.000 1.2599 0.03468 0.02656 -0.0478 0.0240 1.0000
10.250 1.2697 0.03689 0.02883 -0.0459 0.0235 1.0000
10.500 1.2850 0.03871 0.03075 -0.0445 0.0232 1.0000
10.750 1.3046 0.04074 0.03289 -0.0434 0.0230 1.0000
11.000 1.3327 0.04349 0.03580 -0.0430 0.0231 1.0000
11.250 1.3827 0.04829 0.04082 -0.0454 0.0239 1.0000
11.500 1.3974 0.05223 0.04509 -0.0445 0.0238 1.0000
11.750 1.4024 0.05516 0.04827 -0.0425 0.0239 1.0000
12.000 1.4025 0.05658 0.04987 -0.0397 0.0242 1.0000
12.250 1.3970 0.05780 0.05133 -0.0367 0.0248 1.0000
12.500 1.2877 0.05738 0.05150 -0.0292 0.0244 1.0000
12.750 1.2728 0.06054 0.05492 -0.0277 0.0249 1.0000
13.000 1.2490 0.06524 0.06003 -0.0268 0.0263 1.0000
13.250 1.2182 0.07192 0.06712 -0.0270 0.0278 1.0000
13.500 1.1932 0.07837 0.07388 -0.0278 0.0289 1.0000
13.750 1.1678 0.08476 0.08051 -0.0293 0.0296 1.0000
14.000 1.1415 0.09080 0.08677 -0.0314 0.0301 1.0000
14.250 1.1084 0.09659 0.09279 -0.0343 0.0300 1.0000
14.500 1.0815 0.10272 0.09909 -0.0379 0.0301 1.0000
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