GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 402 AIRFOIL (goe402-il) Reynolds number: 500,000 Max Cl/Cd: 105.44 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe402-il-500000-n5.txt Download as CSV file: xf-goe402-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 402 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2730 0.10279 0.10063 -0.0226 1.0000 0.0078
-8.500 -0.2688 0.10026 0.09813 -0.0229 1.0000 0.0078
-8.250 -0.2650 0.09789 0.09578 -0.0230 1.0000 0.0081
-8.000 -0.2525 0.09461 0.09251 -0.0257 0.9929 0.0082
-7.750 -0.2372 0.09117 0.08908 -0.0292 0.9820 0.0088
-7.500 -0.2148 0.08709 0.08500 -0.0350 0.9644 0.0097
-7.250 -0.1708 0.08133 0.07917 -0.0483 0.9312 0.0101
-7.000 -0.1245 0.07569 0.07327 -0.0620 0.8610 0.0102
-6.750 -0.1133 0.07307 0.07034 -0.0644 0.7978 0.0102
-6.500 -0.1020 0.07029 0.06743 -0.0666 0.7727 0.0102
-6.250 -0.0889 0.06734 0.06438 -0.0688 0.7549 0.0102
-6.000 -0.0746 0.06414 0.06110 -0.0711 0.7406 0.0102
-5.750 -0.0641 0.06151 0.05841 -0.0711 0.7288 0.0095
-5.500 -0.0466 0.05834 0.05516 -0.0741 0.7187 0.0088
-5.250 -0.0259 0.05451 0.05125 -0.0779 0.7088 0.0080
-5.000 -0.0026 0.05068 0.04732 -0.0817 0.6998 0.0079
-4.750 0.0221 0.04716 0.04369 -0.0850 0.6910 0.0079
-4.500 0.0487 0.04366 0.04007 -0.0882 0.6814 0.0080
-4.250 0.0760 0.04036 0.03663 -0.0910 0.6711 0.0083
-4.000 0.1050 0.03693 0.03302 -0.0936 0.6608 0.0094
-3.750 0.1360 0.03263 0.02850 -0.0962 0.6517 0.0098
-3.500 0.1680 0.02731 0.02284 -0.0984 0.6444 0.0104
-3.250 0.1953 0.02537 0.02071 -0.0991 0.6355 0.0109
-3.000 0.2230 0.02342 0.01856 -0.0995 0.6266 0.0119
-2.750 0.2537 0.01692 0.01127 -0.0996 0.6193 0.0148
-2.500 0.2801 0.01674 0.01099 -0.0995 0.6080 0.0155
-2.250 0.3068 0.01624 0.01034 -0.0993 0.5967 0.0170
-2.000 0.3345 0.01421 0.00781 -0.0987 0.5867 0.0207
-1.750 0.3610 0.01339 0.00676 -0.0985 0.5760 0.0222
-1.500 0.3876 0.01340 0.00671 -0.0983 0.5652 0.0235
-1.250 0.4144 0.01303 0.00620 -0.0980 0.5547 0.0251
-1.000 0.4411 0.01257 0.00555 -0.0977 0.5436 0.0268
-0.750 0.4680 0.01226 0.00508 -0.0974 0.5318 0.0287
-0.500 0.4946 0.01195 0.00461 -0.0970 0.5181 0.0296
-0.250 0.5211 0.01170 0.00421 -0.0966 0.5029 0.0301
0.000 0.5476 0.01155 0.00394 -0.0963 0.4882 0.0305
0.250 0.5740 0.01146 0.00375 -0.0960 0.4733 0.0311
0.500 0.6002 0.01111 0.00329 -0.0956 0.4588 0.0312
0.750 0.6263 0.01083 0.00293 -0.0952 0.4436 0.0313
1.250 0.6776 0.01041 0.00233 -0.0944 0.4082 0.0330
1.500 0.7033 0.01040 0.00224 -0.0940 0.3896 0.0344
1.750 0.7293 0.01044 0.00222 -0.0936 0.3745 0.0362
2.000 0.7553 0.01050 0.00222 -0.0933 0.3624 0.0377
2.250 0.7812 0.01059 0.00225 -0.0930 0.3511 0.0389
2.500 0.8073 0.01068 0.00229 -0.0926 0.3413 0.0399
2.750 0.8335 0.01077 0.00236 -0.0924 0.3345 0.0417
3.000 0.8598 0.01087 0.00244 -0.0921 0.3283 0.0430
3.250 0.8859 0.01097 0.00250 -0.0918 0.3229 0.0447
3.500 0.9122 0.01104 0.00257 -0.0915 0.3176 0.0496
3.750 0.9378 0.01093 0.00279 -0.0913 0.3125 0.2462
4.250 0.9938 0.00993 0.00318 -0.0919 0.3044 1.0000
4.500 1.0197 0.01010 0.00335 -0.0915 0.3001 1.0000
4.750 1.0452 0.01030 0.00353 -0.0912 0.2958 1.0000
5.000 1.0711 0.01046 0.00370 -0.0909 0.2915 1.0000
5.250 1.0969 0.01063 0.00389 -0.0905 0.2868 1.0000
5.500 1.1224 0.01082 0.00409 -0.0902 0.2829 1.0000
5.750 1.1477 0.01102 0.00431 -0.0898 0.2791 1.0000
6.000 1.1734 0.01118 0.00452 -0.0895 0.2754 1.0000
6.250 1.1988 0.01137 0.00476 -0.0891 0.2709 1.0000
6.500 1.2235 0.01162 0.00501 -0.0887 0.2644 1.0000
6.750 1.2479 0.01188 0.00524 -0.0882 0.2469 1.0000
7.000 1.2708 0.01228 0.00555 -0.0876 0.2220 1.0000
7.250 1.2879 0.01326 0.00615 -0.0862 0.1567 1.0000
7.500 1.3043 0.01431 0.00696 -0.0847 0.1187 1.0000
7.750 1.3251 0.01489 0.00751 -0.0838 0.1050 1.0000
8.000 1.3450 0.01554 0.00809 -0.0827 0.0833 1.0000
8.250 1.3529 0.01729 0.00944 -0.0801 0.0213 1.0000
8.500 1.3711 0.01802 0.01020 -0.0787 0.0129 1.0000
8.750 1.3886 0.01876 0.01101 -0.0773 0.0101 1.0000
9.000 1.4065 0.01943 0.01177 -0.0759 0.0087 1.0000
9.250 1.4235 0.02011 0.01253 -0.0745 0.0076 1.0000
9.500 1.4379 0.02094 0.01343 -0.0726 0.0068 1.0000
9.750 1.4495 0.02188 0.01448 -0.0704 0.0062 1.0000
10.000 1.4599 0.02270 0.01542 -0.0679 0.0059 1.0000
10.250 1.4677 0.02363 0.01646 -0.0651 0.0055 1.0000
10.500 1.4741 0.02466 0.01759 -0.0624 0.0052 1.0000
10.750 1.4793 0.02583 0.01885 -0.0598 0.0049 1.0000
11.000 1.4830 0.02715 0.02027 -0.0573 0.0046 1.0000
11.250 1.4826 0.02891 0.02213 -0.0549 0.0044 1.0000
11.500 1.4806 0.03098 0.02432 -0.0528 0.0042 1.0000
11.750 1.4834 0.03288 0.02633 -0.0516 0.0040 1.0000
12.000 1.4826 0.03531 0.02889 -0.0505 0.0038 1.0000
12.250 1.4805 0.03806 0.03177 -0.0498 0.0037 1.0000
12.500 1.4774 0.04108 0.03493 -0.0494 0.0036 1.0000
12.750 1.4722 0.04451 0.03848 -0.0493 0.0036 1.0000
13.000 1.4679 0.04796 0.04206 -0.0494 0.0034 1.0000
13.250 1.4626 0.05168 0.04590 -0.0497 0.0033 1.0000
13.500 1.4555 0.05576 0.05010 -0.0502 0.0033 1.0000
13.750 1.4485 0.05997 0.05446 -0.0510 0.0032 1.0000
14.000 1.4408 0.06437 0.05899 -0.0519 0.0032 1.0000
14.250 1.4336 0.06887 0.06360 -0.0530 0.0031 1.0000
14.500 1.4264 0.07353 0.06837 -0.0543 0.0030 1.0000
14.750 1.4197 0.07823 0.07318 -0.0558 0.0030 1.0000
15.000 1.4117 0.08326 0.07832 -0.0573 0.0030 1.0000
15.250 1.4050 0.08820 0.08336 -0.0590 0.0029 1.0000
15.500 1.3968 0.09342 0.08869 -0.0608 0.0028 1.0000
15.750 1.3897 0.09853 0.09391 -0.0626 0.0028 1.0000
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Polar data table (+)
Polar graphs
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