GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 403 AIRFOIL (goe403-il) Reynolds number: 200,000 Max Cl/Cd: 72.98 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe403-il-200000-n5.txt Download as CSV file: xf-goe403-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 403 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 -0.3354 0.08996 0.08667 -0.0269 1.0000 0.0133
-7.500 -0.3431 0.08642 0.08323 -0.0280 1.0000 0.0116
-7.250 -0.3442 0.08423 0.08111 -0.0275 1.0000 0.0114
-7.000 -0.3415 0.08179 0.07873 -0.0280 1.0000 0.0113
-6.750 -0.3434 0.07869 0.07567 -0.0280 1.0000 0.0110
-6.500 -0.3377 0.07485 0.07187 -0.0308 0.9982 0.0109
-6.250 -0.3093 0.06886 0.06585 -0.0398 0.9896 0.0107
-6.000 -0.2775 0.06248 0.05941 -0.0495 0.9800 0.0109
-5.750 -0.2429 0.05568 0.05254 -0.0597 0.9697 0.0114
-5.500 -0.2105 0.05013 0.04687 -0.0678 0.9595 0.0126
-5.250 -0.1738 0.04423 0.04079 -0.0757 0.9504 0.0133
-5.000 -0.1350 0.03663 0.03284 -0.0838 0.9411 0.0136
-4.750 -0.0984 0.02478 0.02016 -0.0907 0.9307 0.0142
-4.500 -0.0663 0.01899 0.01338 -0.0930 0.9221 0.0168
-4.250 -0.0337 0.01639 0.01002 -0.0940 0.9138 0.0210
-4.000 -0.0028 0.01560 0.00905 -0.0947 0.9038 0.0261
-3.750 0.0291 0.01481 0.00787 -0.0954 0.8942 0.0330
-3.500 0.0605 0.01463 0.00759 -0.0962 0.8844 0.0394
-3.250 0.0899 0.01386 0.00654 -0.0964 0.8736 0.0445
-3.000 0.1187 0.01321 0.00574 -0.0965 0.8628 0.0477
-2.750 0.1472 0.01273 0.00509 -0.0965 0.8522 0.0507
-2.500 0.1752 0.01232 0.00450 -0.0963 0.8416 0.0532
-2.250 0.2027 0.01200 0.00401 -0.0961 0.8307 0.0553
-2.000 0.2294 0.01166 0.00363 -0.0958 0.8196 0.0601
-1.750 0.2562 0.01142 0.00331 -0.0954 0.8084 0.0644
-1.500 0.2829 0.01121 0.00298 -0.0950 0.7972 0.0693
-1.250 0.3095 0.01101 0.00277 -0.0946 0.7855 0.0814
-1.000 0.3359 0.01087 0.00262 -0.0942 0.7732 0.1007
-0.750 0.3622 0.01076 0.00248 -0.0938 0.7600 0.1200
-0.500 0.3884 0.01067 0.00237 -0.0934 0.7457 0.1383
-0.250 0.4145 0.01056 0.00228 -0.0930 0.7304 0.1613
0.000 0.4401 0.01037 0.00225 -0.0926 0.7133 0.2177
0.250 0.4643 0.00995 0.00225 -0.0920 0.6947 0.3670
0.750 0.5265 0.00873 0.00212 -0.0930 0.6534 1.0000
1.000 0.5519 0.00888 0.00210 -0.0924 0.6326 1.0000
1.250 0.5773 0.00904 0.00211 -0.0918 0.6126 1.0000
1.500 0.6026 0.00922 0.00215 -0.0912 0.5945 1.0000
1.750 0.6281 0.00941 0.00224 -0.0907 0.5783 1.0000
2.000 0.6536 0.00961 0.00234 -0.0902 0.5639 1.0000
2.250 0.6792 0.00980 0.00246 -0.0897 0.5508 1.0000
2.500 0.7050 0.01000 0.00261 -0.0893 0.5392 1.0000
2.750 0.7307 0.01021 0.00281 -0.0889 0.5285 1.0000
3.000 0.7556 0.01045 0.00298 -0.0883 0.5103 1.0000
3.250 0.7789 0.01076 0.00315 -0.0874 0.4779 1.0000
3.500 0.8035 0.01101 0.00337 -0.0868 0.4555 1.0000
3.750 0.8262 0.01137 0.00357 -0.0858 0.4122 1.0000
4.000 0.8454 0.01208 0.00382 -0.0844 0.3217 1.0000
4.250 0.8489 0.01502 0.00515 -0.0814 0.0271 1.0000
4.500 0.8724 0.01555 0.00572 -0.0805 0.0194 1.0000
4.750 0.8957 0.01609 0.00644 -0.0796 0.0158 1.0000
5.000 0.9182 0.01675 0.00728 -0.0786 0.0142 1.0000
5.250 0.9393 0.01756 0.00830 -0.0774 0.0132 1.0000
5.500 0.9546 0.01902 0.01000 -0.0754 0.0117 1.0000
5.750 0.9753 0.01975 0.01080 -0.0742 0.0106 1.0000
6.000 0.9920 0.02092 0.01207 -0.0724 0.0101 1.0000
6.250 1.0080 0.02221 0.01348 -0.0705 0.0098 1.0000
6.500 1.0242 0.02362 0.01496 -0.0686 0.0096 1.0000
6.750 1.0417 0.02516 0.01655 -0.0669 0.0094 1.0000
7.000 1.0614 0.02686 0.01833 -0.0655 0.0093 1.0000
7.250 1.0827 0.02853 0.02009 -0.0644 0.0089 1.0000
7.500 1.1031 0.03011 0.02173 -0.0634 0.0078 1.0000
7.750 1.1250 0.03286 0.02448 -0.0631 0.0071 1.0000
8.000 1.1476 0.03556 0.02736 -0.0623 0.0070 1.0000
8.250 1.1672 0.03776 0.02988 -0.0610 0.0071 1.0000
8.500 1.1849 0.03998 0.03239 -0.0594 0.0072 1.0000
8.750 1.1981 0.04246 0.03545 -0.0565 0.0080 1.0000
9.000 1.2093 0.04619 0.03961 -0.0540 0.0090 1.0000
9.250 1.2142 0.05027 0.04403 -0.0515 0.0100 1.0000
9.500 1.2309 0.05319 0.04727 -0.0494 0.0139 1.0000
9.750 1.2307 0.05637 0.05076 -0.0466 0.0139 1.0000
10.000 1.2267 0.05952 0.05417 -0.0439 0.0139 1.0000
10.250 1.2173 0.06245 0.05733 -0.0407 0.0138 1.0000
10.500 1.2043 0.06539 0.06047 -0.0377 0.0137 1.0000
10.750 1.1900 0.06857 0.06385 -0.0355 0.0137 1.0000
11.000 1.1741 0.07220 0.06766 -0.0343 0.0137 1.0000
11.250 1.1575 0.07624 0.07189 -0.0341 0.0136 1.0000
11.500 1.1402 0.08079 0.07662 -0.0349 0.0137 1.0000
11.750 1.1220 0.08593 0.08194 -0.0367 0.0137 1.0000
12.000 1.1032 0.09177 0.08794 -0.0395 0.0138 1.0000
12.250 1.0838 0.09841 0.09474 -0.0433 0.0139 1.0000
12.500 1.0645 0.10586 0.10234 -0.0482 0.0141 1.0000
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Polar data table (+)
Polar graphs
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