GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.19 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe442-il-1000000-n5.txt Download as CSV file: xf-goe442-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3734 0.11820 0.11650 -0.0198 1.0000 0.0044
-10.500 -0.3668 0.11620 0.11450 -0.0202 1.0000 0.0049
-8.500 -0.4307 0.02167 0.01882 -0.0985 0.9767 0.0049
-8.250 -0.4115 0.01828 0.01503 -0.0988 0.9719 0.0051
-8.000 -0.3854 0.01643 0.01291 -0.0994 0.9690 0.0053
-7.750 -0.3568 0.01504 0.01127 -0.1002 0.9665 0.0054
-7.500 -0.3295 0.01394 0.00998 -0.1005 0.9635 0.0056
-7.250 -0.3041 0.01324 0.00914 -0.1002 0.9590 0.0058
-7.000 -0.2755 0.01256 0.00833 -0.1004 0.9551 0.0060
-6.750 -0.2468 0.01161 0.00719 -0.1008 0.9514 0.0063
-6.500 -0.2217 0.01101 0.00650 -0.1002 0.9452 0.0066
-6.250 -0.1933 0.01052 0.00591 -0.1003 0.9397 0.0070
-6.000 -0.1658 0.01011 0.00542 -0.1002 0.9329 0.0074
-5.750 -0.1382 0.00968 0.00489 -0.1000 0.9247 0.0077
-5.500 -0.1110 0.00932 0.00444 -0.0997 0.9142 0.0082
-5.250 -0.0836 0.00902 0.00403 -0.0994 0.9007 0.0085
-5.000 -0.0569 0.00864 0.00352 -0.0990 0.8846 0.0093
-4.750 -0.0304 0.00839 0.00319 -0.0985 0.8672 0.0103
-4.500 -0.0042 0.00821 0.00290 -0.0979 0.8475 0.0113
-4.250 0.0215 0.00807 0.00263 -0.0972 0.8244 0.0122
-4.000 0.0467 0.00791 0.00235 -0.0965 0.7986 0.0143
-3.750 0.0717 0.00784 0.00215 -0.0957 0.7717 0.0163
-3.500 0.0967 0.00779 0.00201 -0.0949 0.7446 0.0203
-3.250 0.1219 0.00780 0.00189 -0.0941 0.7159 0.0234
-3.000 0.1472 0.00781 0.00181 -0.0934 0.6878 0.0271
-2.750 0.1723 0.00787 0.00174 -0.0927 0.6531 0.0297
-2.500 0.1969 0.00801 0.00169 -0.0919 0.6083 0.0311
-2.250 0.2217 0.00807 0.00159 -0.0911 0.5696 0.0343
-2.000 0.2476 0.00812 0.00155 -0.0906 0.5450 0.0368
-1.750 0.2739 0.00816 0.00151 -0.0901 0.5270 0.0390
-1.500 0.3000 0.00824 0.00148 -0.0897 0.5068 0.0404
-1.250 0.3264 0.00822 0.00138 -0.0892 0.4910 0.0422
-1.000 0.3530 0.00820 0.00131 -0.0888 0.4781 0.0453
-0.750 0.3800 0.00818 0.00127 -0.0885 0.4689 0.0482
-0.500 0.4068 0.00820 0.00124 -0.0882 0.4580 0.0509
-0.250 0.4334 0.00824 0.00122 -0.0878 0.4445 0.0528
0.000 0.4601 0.00824 0.00119 -0.0874 0.4327 0.0583
0.250 0.4869 0.00826 0.00118 -0.0871 0.4213 0.0633
0.500 0.5136 0.00830 0.00118 -0.0867 0.4096 0.0670
0.750 0.5399 0.00835 0.00118 -0.0863 0.3945 0.0762
1.000 0.5662 0.00837 0.00120 -0.0860 0.3803 0.0978
1.250 0.5916 0.00821 0.00127 -0.0855 0.3694 0.2144
1.500 0.6174 0.00817 0.00135 -0.0851 0.3575 0.2845
1.750 0.6434 0.00819 0.00142 -0.0847 0.3446 0.3296
2.000 0.6681 0.00803 0.00153 -0.0842 0.3314 0.4634
2.500 0.7418 0.00724 0.00181 -0.0885 0.3014 1.0000
2.750 0.7672 0.00738 0.00189 -0.0879 0.2912 1.0000
3.000 0.7923 0.00754 0.00199 -0.0873 0.2795 1.0000
3.250 0.8174 0.00772 0.00209 -0.0867 0.2661 1.0000
3.500 0.8421 0.00793 0.00222 -0.0860 0.2484 1.0000
3.750 0.8660 0.00822 0.00238 -0.0852 0.2224 1.0000
4.000 0.8886 0.00866 0.00261 -0.0842 0.1843 1.0000
4.250 0.9119 0.00902 0.00285 -0.0834 0.1586 1.0000
4.500 0.9359 0.00932 0.00306 -0.0827 0.1427 1.0000
4.750 0.9608 0.00954 0.00324 -0.0821 0.1346 1.0000
5.000 0.9854 0.00977 0.00344 -0.0814 0.1274 1.0000
5.250 1.0106 0.00996 0.00362 -0.0809 0.1237 1.0000
5.500 1.0356 0.01015 0.00381 -0.0803 0.1205 1.0000
5.750 1.0604 0.01036 0.00401 -0.0798 0.1174 1.0000
6.000 1.0851 0.01058 0.00423 -0.0792 0.1143 1.0000
6.250 1.1098 0.01080 0.00446 -0.0786 0.1115 1.0000
6.500 1.1348 0.01098 0.00467 -0.0781 0.1106 1.0000
6.750 1.1595 0.01117 0.00489 -0.0775 0.1082 1.0000
7.000 1.1837 0.01142 0.00514 -0.0769 0.1040 1.0000
7.250 1.2072 0.01173 0.00542 -0.0762 0.0978 1.0000
7.500 1.2318 0.01191 0.00564 -0.0756 0.0955 1.0000
7.750 1.2560 0.01214 0.00589 -0.0750 0.0921 1.0000
8.000 1.2789 0.01248 0.00618 -0.0742 0.0839 1.0000
8.250 1.3015 0.01283 0.00649 -0.0734 0.0735 1.0000
8.500 1.3200 0.01354 0.00703 -0.0720 0.0487 1.0000
8.750 1.3354 0.01452 0.00786 -0.0701 0.0253 1.0000
9.000 1.3523 0.01533 0.00860 -0.0684 0.0126 1.0000
9.250 1.3724 0.01583 0.00912 -0.0672 0.0099 1.0000
9.500 1.3920 0.01635 0.00969 -0.0659 0.0082 1.0000
9.750 1.4118 0.01682 0.01020 -0.0647 0.0073 1.0000
10.000 1.4303 0.01737 0.01079 -0.0633 0.0065 1.0000
10.250 1.4484 0.01793 0.01139 -0.0618 0.0058 1.0000
10.500 1.4663 0.01846 0.01198 -0.0603 0.0054 1.0000
10.750 1.4833 0.01902 0.01259 -0.0587 0.0049 1.0000
11.000 1.4978 0.01964 0.01325 -0.0567 0.0045 1.0000
11.250 1.5094 0.02034 0.01403 -0.0541 0.0041 1.0000
11.500 1.5219 0.02096 0.01472 -0.0518 0.0039 1.0000
11.750 1.5337 0.02163 0.01546 -0.0495 0.0037 1.0000
12.000 1.5446 0.02236 0.01626 -0.0471 0.0036 1.0000
12.250 1.5547 0.02315 0.01712 -0.0447 0.0033 1.0000
12.500 1.5640 0.02401 0.01805 -0.0424 0.0032 1.0000
12.750 1.5718 0.02500 0.01911 -0.0400 0.0031 1.0000
13.000 1.5777 0.02614 0.02033 -0.0376 0.0029 1.0000
13.250 1.5815 0.02748 0.02178 -0.0352 0.0028 1.0000
13.500 1.5829 0.02906 0.02347 -0.0328 0.0027 1.0000
13.750 1.5878 0.03046 0.02497 -0.0309 0.0026 1.0000
14.000 1.5892 0.03224 0.02686 -0.0291 0.0026 1.0000
14.250 1.5904 0.03416 0.02888 -0.0276 0.0025 1.0000
14.500 1.5914 0.03623 0.03106 -0.0265 0.0024 1.0000
14.750 1.5890 0.03883 0.03376 -0.0256 0.0024 1.0000
15.000 1.5875 0.04151 0.03655 -0.0251 0.0023 1.0000
15.250 1.5840 0.04462 0.03978 -0.0250 0.0023 1.0000
15.500 1.5779 0.04830 0.04359 -0.0255 0.0022 1.0000
15.750 1.5691 0.05260 0.04802 -0.0264 0.0022 1.0000
16.000 1.5620 0.05696 0.05249 -0.0278 0.0021 1.0000
16.250 1.5445 0.06312 0.05882 -0.0300 0.0022 1.0000
16.500 1.5363 0.06794 0.06375 -0.0318 0.0021 1.0000
16.750 1.5174 0.07463 0.07059 -0.0346 0.0021 1.0000
17.000 1.5040 0.08052 0.07660 -0.0370 0.0021 1.0000
17.250 1.4845 0.08767 0.08388 -0.0402 0.0020 1.0000
17.500 1.4635 0.09532 0.09168 -0.0437 0.0021 1.0000
17.750 1.4381 0.10409 0.10060 -0.0480 0.0021 1.0000
18.000 1.4173 0.11225 0.10889 -0.0520 0.0021 1.0000
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