GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 406 AIRFOIL (goe406-il) Reynolds number: 200,000 Max Cl/Cd: 68.09 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe406-il-200000-n5.txt Download as CSV file: xf-goe406-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 406 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1450 0.09543 0.09175 -0.0656 0.9627 0.0353
-8.750 -0.1366 0.09208 0.08842 -0.0688 0.9526 0.0362
-8.500 -0.1351 0.08874 0.08509 -0.0735 0.9367 0.0367
-8.000 -0.1113 0.08193 0.07828 -0.0776 0.9070 0.0375
-7.750 -0.0914 0.07853 0.07485 -0.0811 0.8937 0.0382
-7.500 -0.0675 0.07459 0.07085 -0.0874 0.8810 0.0391
-7.250 -0.0396 0.07019 0.06636 -0.0956 0.8688 0.0404
-7.000 -0.0140 0.06434 0.06027 -0.1094 0.8510 0.0422
-6.750 0.0094 0.05986 0.05560 -0.1156 0.8379 0.0425
-6.500 0.0312 0.05734 0.05304 -0.1164 0.8275 0.0431
-6.250 0.0511 0.05512 0.05072 -0.1178 0.8174 0.0442
-6.000 0.0658 0.05273 0.04821 -0.1190 0.8074 0.0459
-5.750 0.0729 0.04922 0.04423 -0.1210 0.7970 0.0484
-5.500 0.0868 0.04670 0.04169 -0.1204 0.7890 0.0488
-5.250 0.1003 0.04481 0.03976 -0.1194 0.7811 0.0493
-5.000 0.1139 0.04308 0.03797 -0.1183 0.7725 0.0500
-4.750 0.1280 0.04132 0.03607 -0.1172 0.7647 0.0510
-4.250 0.1544 0.03706 0.03112 -0.1134 0.7499 0.0554
-3.750 0.1777 0.03103 0.02465 -0.1081 0.7359 0.0428
-3.250 0.2052 0.02626 0.01921 -0.1022 0.7219 0.0368
-3.000 0.2239 0.02496 0.01773 -0.1005 0.7153 0.0365
-2.750 0.2403 0.02369 0.01629 -0.0982 0.7069 0.0362
-2.500 0.2591 0.02237 0.01470 -0.0961 0.6994 0.0359
-2.250 0.2785 0.02115 0.01324 -0.0942 0.6924 0.0357
-2.000 0.2993 0.01998 0.01180 -0.0924 0.6861 0.0357
-1.750 0.3227 0.01903 0.01058 -0.0912 0.6804 0.0359
-1.500 0.3452 0.01826 0.00954 -0.0897 0.6737 0.0368
-1.250 0.3692 0.01756 0.00869 -0.0887 0.6670 0.0372
-1.000 0.3943 0.01693 0.00793 -0.0880 0.6607 0.0373
-0.750 0.4185 0.01638 0.00732 -0.0871 0.6534 0.0376
-0.500 0.4439 0.01592 0.00676 -0.0864 0.6466 0.0379
-0.250 0.4677 0.01552 0.00635 -0.0855 0.6388 0.0383
0.000 0.4919 0.01517 0.00595 -0.0845 0.6306 0.0387
0.250 0.5148 0.01488 0.00564 -0.0834 0.6219 0.0393
0.500 0.5378 0.01462 0.00535 -0.0822 0.6133 0.0401
0.750 0.5599 0.01443 0.00515 -0.0809 0.6041 0.0413
1.000 0.5819 0.01426 0.00492 -0.0795 0.5945 0.0428
1.250 0.6027 0.01412 0.00481 -0.0780 0.5832 0.0444
1.500 0.6234 0.01402 0.00468 -0.0764 0.5711 0.0457
1.750 0.6436 0.01397 0.00456 -0.0746 0.5574 0.0473
2.000 0.6632 0.01394 0.00448 -0.0728 0.5419 0.0492
2.250 0.6822 0.01396 0.00444 -0.0708 0.5253 0.0525
2.500 0.7006 0.01400 0.00444 -0.0688 0.5071 0.0593
2.750 0.7177 0.01405 0.00447 -0.0665 0.4873 0.0849
3.250 0.9533 0.01400 0.00571 -0.1079 0.4106 1.0000
3.500 0.9713 0.01432 0.00592 -0.1060 0.3974 1.0000
3.750 0.9898 0.01463 0.00614 -0.1042 0.3870 1.0000
4.250 1.0269 0.01526 0.00663 -0.1006 0.3706 1.0000
4.500 1.0450 0.01560 0.00689 -0.0987 0.3637 1.0000
4.750 1.0637 0.01591 0.00716 -0.0970 0.3580 1.0000
5.000 1.0828 0.01621 0.00744 -0.0954 0.3524 1.0000
5.250 1.1008 0.01655 0.00773 -0.0935 0.3472 1.0000
5.500 1.1188 0.01691 0.00804 -0.0917 0.3430 1.0000
5.750 1.1380 0.01719 0.00834 -0.0902 0.3383 1.0000
6.000 1.1560 0.01750 0.00867 -0.0884 0.3343 1.0000
6.250 1.1730 0.01784 0.00899 -0.0864 0.3307 1.0000
6.500 1.1897 0.01822 0.00933 -0.0844 0.3277 1.0000
6.750 1.2080 0.01854 0.00968 -0.0827 0.3247 1.0000
7.000 1.2262 0.01885 0.01004 -0.0810 0.3216 1.0000
7.250 1.2443 0.01918 0.01041 -0.0793 0.3188 1.0000
7.500 1.2621 0.01954 0.01079 -0.0776 0.3160 1.0000
7.750 1.2799 0.01992 0.01120 -0.0760 0.3134 1.0000
8.000 1.2977 0.02036 0.01162 -0.0744 0.3103 1.0000
8.250 1.3143 0.02071 0.01205 -0.0725 0.3069 1.0000
8.500 1.3290 0.02106 0.01248 -0.0703 0.3021 1.0000
8.750 1.3422 0.02147 0.01292 -0.0679 0.2969 1.0000
9.000 1.3562 0.02196 0.01338 -0.0658 0.2923 1.0000
9.250 1.3703 0.02234 0.01389 -0.0637 0.2877 1.0000
9.500 1.3846 0.02277 0.01440 -0.0616 0.2834 1.0000
9.750 1.3981 0.02326 0.01494 -0.0596 0.2794 1.0000
10.000 1.4118 0.02381 0.01550 -0.0576 0.2759 1.0000
10.250 1.4258 0.02428 0.01612 -0.0557 0.2716 1.0000
10.500 1.4369 0.02483 0.01676 -0.0534 0.2658 1.0000
10.750 1.4456 0.02553 0.01747 -0.0509 0.2601 1.0000
11.000 1.4582 0.02612 0.01821 -0.0491 0.2544 1.0000
11.250 1.4676 0.02685 0.01902 -0.0469 0.2478 1.0000
11.500 1.4762 0.02767 0.01991 -0.0447 0.2413 1.0000
11.750 1.4840 0.02858 0.02092 -0.0426 0.2319 1.0000
12.000 1.4912 0.02960 0.02202 -0.0406 0.2219 1.0000
12.250 1.4963 0.03082 0.02328 -0.0385 0.2099 1.0000
12.500 1.4974 0.03240 0.02484 -0.0364 0.1900 1.0000
12.750 1.4899 0.03473 0.02705 -0.0338 0.1593 1.0000
13.000 1.4708 0.03823 0.03030 -0.0309 0.1263 1.0000
13.250 1.4579 0.04147 0.03346 -0.0288 0.1084 1.0000
13.500 1.4461 0.04478 0.03674 -0.0270 0.0886 1.0000
13.750 1.4298 0.04870 0.04060 -0.0254 0.0682 1.0000
14.000 1.4176 0.05242 0.04431 -0.0243 0.0591 1.0000
14.250 1.4060 0.05625 0.04818 -0.0234 0.0534 1.0000
14.500 1.3979 0.05986 0.05189 -0.0229 0.0501 1.0000
14.750 1.3854 0.06415 0.05625 -0.0227 0.0470 1.0000
15.000 1.3773 0.06806 0.06029 -0.0226 0.0452 1.0000
15.250 1.3680 0.07227 0.06462 -0.0228 0.0436 1.0000
15.500 1.3572 0.07680 0.06927 -0.0232 0.0420 1.0000
15.750 1.3454 0.08164 0.07422 -0.0238 0.0411 1.0000
16.000 1.3317 0.08685 0.07956 -0.0247 0.0400 1.0000
16.250 1.3184 0.09214 0.08495 -0.0257 0.0391 1.0000
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Polar data table (+)
Polar graphs
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