GOE 559 AIRFOIL (goe559-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 559 AIRFOIL (goe559-il) Reynolds number: 50,000 Max Cl/Cd: 28.64 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe559-il-50000-n5.txt Download as CSV file: xf-goe559-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 559 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3657 0.10249 0.09670 -0.0403 1.0000 0.1048
-8.250 -0.3583 0.09859 0.09286 -0.0389 1.0000 0.1138
-8.000 -0.3712 0.09655 0.09099 -0.0406 1.0000 0.1185
-7.750 -0.3663 0.09324 0.08775 -0.0390 1.0000 0.1286
-7.500 -0.3855 0.09131 0.08603 -0.0400 1.0000 0.1323
-7.250 -0.3857 0.08835 0.08318 -0.0383 1.0000 0.1450
-7.000 -0.3905 0.08576 0.08072 -0.0370 1.0000 0.1585
-6.750 -0.4005 0.08343 0.07853 -0.0359 1.0000 0.1739
-6.500 -0.2831 0.06790 0.06363 -0.0242 0.9882 0.3319
-6.250 -0.4073 0.07951 0.07491 -0.0265 1.0000 0.2408
-4.750 -0.3031 0.05577 0.05101 -0.0449 0.9125 0.3624
-4.500 -0.2350 0.04509 0.03856 -0.0681 0.8928 0.1584
-4.250 -0.1904 0.04196 0.03437 -0.0698 0.8768 0.1042
-4.000 -0.1532 0.03989 0.03153 -0.0697 0.8592 0.0774
-3.750 -0.1196 0.03695 0.02816 -0.0698 0.8428 0.0624
-3.500 -0.0850 0.03500 0.02559 -0.0695 0.8266 0.0511
-3.250 -0.0529 0.03235 0.02255 -0.0696 0.8111 0.0444
-3.000 -0.0188 0.03096 0.02051 -0.0691 0.7957 0.0388
-2.750 0.0133 0.02890 0.01813 -0.0690 0.7808 0.0354
-2.500 0.0460 0.02776 0.01650 -0.0684 0.7661 0.0320
-2.250 0.0778 0.02633 0.01481 -0.0680 0.7529 0.0304
-2.000 0.1073 0.02513 0.01330 -0.0675 0.7398 0.0298
-1.750 0.1343 0.02435 0.01211 -0.0669 0.7269 0.0310
-1.500 0.1584 0.02346 0.01088 -0.0661 0.7146 0.0333
-1.250 0.1836 0.02293 0.00995 -0.0655 0.7033 0.0349
-1.000 0.2097 0.02255 0.00918 -0.0650 0.6928 0.0370
-0.750 0.2364 0.02214 0.00826 -0.0645 0.6833 0.0473
-0.500 0.3247 0.01904 0.00773 -0.0755 0.6722 1.0000
-0.250 0.3470 0.01928 0.00752 -0.0747 0.6629 1.0000
0.000 0.3704 0.01950 0.00737 -0.0742 0.6550 1.0000
0.250 0.3925 0.01980 0.00741 -0.0736 0.6460 1.0000
0.500 0.4164 0.02006 0.00739 -0.0732 0.6388 1.0000
0.750 0.4390 0.02037 0.00756 -0.0727 0.6309 1.0000
1.000 0.4629 0.02066 0.00773 -0.0724 0.6246 1.0000
1.250 0.4852 0.02103 0.00808 -0.0719 0.6175 1.0000
1.500 0.5100 0.02132 0.00837 -0.0716 0.6123 1.0000
1.750 0.5312 0.02177 0.00891 -0.0710 0.6054 1.0000
2.000 0.5551 0.02211 0.00935 -0.0706 0.6000 1.0000
2.250 0.5776 0.02255 0.00999 -0.0701 0.5944 1.0000
2.500 0.5960 0.02208 0.00948 -0.0672 0.5682 1.0000
2.750 0.5996 0.02132 0.00830 -0.0610 0.5083 1.0000
3.000 0.6088 0.02132 0.00834 -0.0571 0.4571 1.0000
3.250 0.6194 0.02163 0.00842 -0.0540 0.3833 1.0000
3.500 0.6129 0.02456 0.00965 -0.0497 0.0387 1.0000
3.750 0.6312 0.02540 0.01067 -0.0482 0.0336 1.0000
4.000 0.6486 0.02628 0.01184 -0.0466 0.0310 1.0000
4.250 0.6632 0.02738 0.01324 -0.0448 0.0286 1.0000
4.500 0.6730 0.02885 0.01507 -0.0424 0.0264 1.0000
4.750 0.6827 0.03016 0.01669 -0.0401 0.0261 1.0000
5.000 0.6885 0.03169 0.01848 -0.0375 0.0261 1.0000
5.250 0.6900 0.03338 0.02042 -0.0346 0.0265 1.0000
5.500 0.6864 0.03523 0.02247 -0.0312 0.0267 1.0000
5.750 0.6808 0.03738 0.02478 -0.0283 0.0270 1.0000
6.000 0.6799 0.03944 0.02701 -0.0263 0.0273 1.0000
6.250 0.6829 0.04138 0.02913 -0.0246 0.0281 1.0000
6.500 0.6867 0.04333 0.03122 -0.0233 0.0287 1.0000
6.750 0.6925 0.04513 0.03323 -0.0215 0.0300 1.0000
7.000 0.7034 0.04641 0.03458 -0.0190 0.0317 1.0000
7.250 0.8415 0.04431 0.03244 -0.0188 0.0387 1.0000
7.500 0.9703 0.04802 0.03621 -0.0268 0.0564 1.0000
7.750 1.0063 0.04910 0.03775 -0.0254 0.0691 1.0000
8.000 1.0462 0.05040 0.03957 -0.0241 0.0861 1.0000
8.250 1.0956 0.05275 0.04228 -0.0241 0.1057 1.0000
8.500 1.1237 0.05452 0.04465 -0.0219 0.1191 1.0000
8.750 1.1498 0.05727 0.04795 -0.0200 0.1317 1.0000
9.250 1.1615 0.06162 0.05358 -0.0136 0.1480 1.0000
9.500 1.1581 0.06497 0.05740 -0.0106 0.1528 1.0000
9.750 1.1608 0.06921 0.06191 -0.0088 0.1556 1.0000
10.000 1.1675 0.07452 0.06739 -0.0077 0.1573 1.0000
10.250 1.0254 0.06475 0.05850 0.0043 0.1593 1.0000
10.500 0.9943 0.06859 0.06250 0.0067 0.1594 1.0000
10.750 0.9629 0.07320 0.06724 0.0077 0.1590 1.0000
11.000 0.9320 0.07856 0.07269 0.0077 0.1585 1.0000
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Polar data table (+)
Polar graphs
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