GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.24 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe187-il-1000000-n5.txt Download as CSV file: xf-goe187-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3318 0.11005 0.10849 -0.0151 1.0000 0.0033
-9.000 -0.3252 0.10683 0.10529 -0.0166 1.0000 0.0033
-8.750 -0.3188 0.10364 0.10211 -0.0181 1.0000 0.0033
-6.750 -0.2509 0.07754 0.07522 -0.0363 0.7388 0.0035
-6.500 -0.2353 0.07424 0.07185 -0.0402 0.7239 0.0037
-6.250 -0.2173 0.07072 0.06825 -0.0445 0.7106 0.0038
-6.000 -0.1972 0.06705 0.06451 -0.0491 0.6983 0.0039
-5.750 -0.1752 0.06327 0.06066 -0.0538 0.6871 0.0040
-5.500 -0.1515 0.05949 0.05680 -0.0583 0.6779 0.0042
-5.250 -0.1261 0.05570 0.05293 -0.0626 0.6700 0.0043
-5.000 -0.0993 0.05195 0.04909 -0.0666 0.6636 0.0045
-4.750 -0.0708 0.04824 0.04528 -0.0703 0.6566 0.0048
-4.500 -0.0390 0.04456 0.04146 -0.0737 0.6501 0.0051
-4.250 -0.0084 0.04103 0.03778 -0.0764 0.6426 0.0052
-4.000 0.0216 0.03766 0.03425 -0.0784 0.6358 0.0052
-3.750 0.0508 0.03450 0.03092 -0.0799 0.6283 0.0052
-3.250 0.1054 0.02845 0.02452 -0.0823 0.6150 0.0045
-3.000 0.1357 0.02550 0.02133 -0.0828 0.6084 0.0042
-2.750 0.1658 0.02293 0.01852 -0.0831 0.6011 0.0044
-2.500 0.1959 0.02059 0.01591 -0.0831 0.5932 0.0046
-2.250 0.2264 0.01843 0.01348 -0.0827 0.5836 0.0051
-2.000 0.2556 0.01647 0.01123 -0.0827 0.5740 0.0048
-1.750 0.2852 0.01457 0.00903 -0.0824 0.5631 0.0047
-1.500 0.3150 0.01246 0.00656 -0.0819 0.5515 0.0046
-1.250 0.3438 0.01001 0.00371 -0.0813 0.5373 0.0050
-1.000 0.3714 0.00935 0.00282 -0.0812 0.5134 0.0055
-0.750 0.3986 0.00926 0.00254 -0.0811 0.4757 0.0061
-0.500 0.4260 0.00938 0.00252 -0.0811 0.4442 0.0072
-0.250 0.4538 0.00919 0.00217 -0.0811 0.4253 0.0080
0.000 0.4816 0.00900 0.00184 -0.0812 0.4082 0.0093
0.250 0.5095 0.00903 0.00181 -0.0812 0.3930 0.0114
0.500 0.5375 0.00907 0.00178 -0.0813 0.3809 0.0133
0.750 0.5657 0.00899 0.00162 -0.0814 0.3717 0.0188
1.000 0.5936 0.00904 0.00161 -0.0814 0.3618 0.0238
1.250 0.6217 0.00907 0.00159 -0.0815 0.3535 0.0275
1.500 0.6496 0.00911 0.00159 -0.0816 0.3451 0.0341
2.000 0.7033 0.00726 0.00182 -0.0821 0.3293 1.0000
2.250 0.7310 0.00738 0.00187 -0.0821 0.3220 1.0000
2.500 0.7588 0.00750 0.00193 -0.0822 0.3164 1.0000
2.750 0.7865 0.00761 0.00200 -0.0822 0.3100 1.0000
3.000 0.8140 0.00775 0.00208 -0.0823 0.3034 1.0000
3.250 0.8417 0.00786 0.00217 -0.0824 0.2976 1.0000
3.500 0.8692 0.00800 0.00226 -0.0824 0.2909 1.0000
3.750 0.8966 0.00813 0.00236 -0.0825 0.2840 1.0000
4.000 0.9237 0.00831 0.00249 -0.0825 0.2733 1.0000
4.250 0.9507 0.00850 0.00262 -0.0825 0.2615 1.0000
4.500 0.9776 0.00871 0.00277 -0.0825 0.2479 1.0000
4.750 1.0037 0.00901 0.00297 -0.0824 0.2249 1.0000
5.000 1.0270 0.00968 0.00337 -0.0820 0.1739 1.0000
5.250 1.0523 0.01006 0.00366 -0.0818 0.1553 1.0000
5.500 1.0781 0.01037 0.00393 -0.0816 0.1418 1.0000
5.750 1.1028 0.01081 0.00425 -0.0814 0.1187 1.0000
6.000 1.1269 0.01132 0.00463 -0.0810 0.0936 1.0000
6.250 1.1520 0.01168 0.00495 -0.0808 0.0858 1.0000
6.500 1.1775 0.01197 0.00525 -0.0806 0.0795 1.0000
6.750 1.2024 0.01232 0.00559 -0.0803 0.0734 1.0000
7.000 1.2275 0.01262 0.00590 -0.0801 0.0682 1.0000
7.250 1.2458 0.01374 0.00672 -0.0790 0.0194 1.0000
7.500 1.2678 0.01438 0.00737 -0.0783 0.0067 1.0000
7.750 1.2911 0.01484 0.00787 -0.0777 0.0047 1.0000
8.000 1.3139 0.01533 0.00840 -0.0772 0.0036 1.0000
8.250 1.3366 0.01580 0.00893 -0.0766 0.0029 1.0000
8.500 1.3578 0.01640 0.00958 -0.0758 0.0025 1.0000
8.750 1.3790 0.01698 0.01023 -0.0749 0.0022 1.0000
9.000 1.3995 0.01759 0.01091 -0.0740 0.0020 1.0000
9.250 1.4191 0.01824 0.01166 -0.0730 0.0018 1.0000
9.500 1.4378 0.01893 0.01242 -0.0719 0.0016 1.0000
9.750 1.4534 0.01986 0.01344 -0.0703 0.0014 1.0000
10.000 1.4705 0.02057 0.01423 -0.0690 0.0013 1.0000
10.250 1.4849 0.02144 0.01519 -0.0672 0.0012 1.0000
10.500 1.4967 0.02238 0.01623 -0.0651 0.0011 1.0000
10.750 1.5041 0.02336 0.01732 -0.0623 0.0010 1.0000
11.000 1.5105 0.02445 0.01849 -0.0595 0.0010 1.0000
11.250 1.5163 0.02566 0.01981 -0.0570 0.0009 1.0000
11.500 1.5212 0.02705 0.02130 -0.0547 0.0009 1.0000
11.750 1.5255 0.02863 0.02298 -0.0528 0.0008 1.0000
12.000 1.5276 0.03052 0.02499 -0.0510 0.0008 1.0000
12.250 1.5271 0.03284 0.02742 -0.0495 0.0007 1.0000
12.500 1.5223 0.03580 0.03052 -0.0483 0.0007 1.0000
12.750 1.5118 0.03965 0.03454 -0.0475 0.0007 1.0000
13.000 1.5093 0.04280 0.03785 -0.0473 0.0007 1.0000
13.250 1.5049 0.04632 0.04150 -0.0472 0.0007 1.0000
13.500 1.4989 0.05010 0.04542 -0.0473 0.0006 1.0000
13.750 1.4908 0.05428 0.04974 -0.0477 0.0006 1.0000
14.000 1.4806 0.05883 0.05443 -0.0483 0.0006 1.0000
14.250 1.4700 0.06357 0.05931 -0.0490 0.0006 1.0000
14.500 1.4592 0.06857 0.06443 -0.0501 0.0006 1.0000
14.750 1.4470 0.07390 0.06990 -0.0514 0.0006 1.0000
15.000 1.4349 0.07941 0.07555 -0.0529 0.0006 1.0000
15.250 1.4226 0.08510 0.08137 -0.0545 0.0006 1.0000
15.500 1.4102 0.09085 0.08724 -0.0562 0.0006 1.0000
15.750 1.3970 0.09685 0.09338 -0.0582 0.0005 1.0000
16.000 1.3846 0.10281 0.09946 -0.0601 0.0005 1.0000
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Polar data table (+)
Polar graphs
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