GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.69 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe517-il-1000000-n5.txt Download as CSV file: xf-goe517-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 517 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3355 0.11201 0.11036 -0.0255 1.0000 0.0045
-9.750 -0.3315 0.10883 0.10720 -0.0264 1.0000 0.0045
-9.500 -0.3283 0.10558 0.10396 -0.0272 1.0000 0.0045
-9.250 -0.3247 0.10269 0.10110 -0.0277 1.0000 0.0045
-9.000 -0.3202 0.10074 0.09916 -0.0275 1.0000 0.0041
-8.750 -0.3118 0.09715 0.09558 -0.0298 0.9992 0.0038
-8.500 -0.3024 0.09345 0.09189 -0.0324 0.9912 0.0049
-8.250 -0.1595 0.06740 0.06580 -0.0569 0.9385 0.0043
-8.000 -0.1477 0.06309 0.06140 -0.0605 0.9115 0.0042
-7.750 -0.2504 0.07993 0.07835 -0.0487 0.9609 0.0044
-7.500 -0.2174 0.07473 0.07310 -0.0589 0.9476 0.0042
-7.250 -0.1841 0.06930 0.06756 -0.0698 0.9180 0.0039
-7.000 -0.1724 0.06538 0.06349 -0.0740 0.8822 0.0037
-6.750 -0.1652 0.06180 0.05978 -0.0765 0.8572 0.0038
-5.750 -0.1465 0.01536 0.01137 -0.0936 0.8077 0.0040
-5.500 -0.1237 0.01354 0.00916 -0.0930 0.8016 0.0043
-5.000 -0.0741 0.01148 0.00656 -0.0919 0.7903 0.0046
-4.750 -0.0490 0.01062 0.00549 -0.0914 0.7841 0.0049
-4.500 -0.0230 0.01017 0.00492 -0.0910 0.7782 0.0052
-4.250 0.0035 0.00974 0.00438 -0.0907 0.7715 0.0055
-4.000 0.0296 0.00935 0.00386 -0.0903 0.7645 0.0059
-3.750 0.0562 0.00899 0.00340 -0.0899 0.7569 0.0063
-3.500 0.0822 0.00865 0.00294 -0.0895 0.7473 0.0067
-3.250 0.1085 0.00841 0.00264 -0.0891 0.7349 0.0075
-3.000 0.1348 0.00823 0.00238 -0.0887 0.7213 0.0084
-2.750 0.1611 0.00803 0.00207 -0.0883 0.7076 0.0092
-2.500 0.1869 0.00786 0.00182 -0.0878 0.6887 0.0106
-2.250 0.2125 0.00780 0.00163 -0.0872 0.6644 0.0120
-2.000 0.2376 0.00773 0.00145 -0.0866 0.6357 0.0149
-1.750 0.2627 0.00773 0.00130 -0.0860 0.6052 0.0183
-1.500 0.2879 0.00773 0.00119 -0.0854 0.5769 0.0246
-0.750 0.3659 0.00767 0.00105 -0.0843 0.5316 0.0700
-0.500 0.3925 0.00768 0.00103 -0.0840 0.5236 0.0787
-0.250 0.4194 0.00767 0.00101 -0.0838 0.5164 0.0864
0.000 0.4460 0.00768 0.00100 -0.0835 0.5090 0.0959
0.250 0.4730 0.00768 0.00099 -0.0834 0.5019 0.1012
0.500 0.4998 0.00769 0.00099 -0.0831 0.4955 0.1098
0.750 0.5266 0.00769 0.00099 -0.0829 0.4899 0.1188
1.000 0.5534 0.00770 0.00101 -0.0827 0.4824 0.1308
1.250 0.5800 0.00771 0.00103 -0.0825 0.4746 0.1485
1.500 0.6065 0.00770 0.00107 -0.0823 0.4663 0.1768
1.750 0.6327 0.00767 0.00113 -0.0820 0.4583 0.2253
2.000 0.6561 0.00726 0.00124 -0.0814 0.4482 0.4747
2.500 0.7464 0.00644 0.00148 -0.0897 0.4067 1.0000
2.750 0.7700 0.00666 0.00157 -0.0889 0.3822 1.0000
3.000 0.7936 0.00687 0.00169 -0.0881 0.3599 1.0000
3.250 0.8174 0.00709 0.00182 -0.0874 0.3416 1.0000
3.500 0.8414 0.00728 0.00195 -0.0866 0.3272 1.0000
3.750 0.8655 0.00747 0.00209 -0.0859 0.3156 1.0000
4.000 0.8895 0.00767 0.00224 -0.0852 0.3028 1.0000
4.250 0.9139 0.00784 0.00238 -0.0846 0.2924 1.0000
4.500 0.9381 0.00802 0.00254 -0.0840 0.2828 1.0000
4.750 0.9627 0.00818 0.00269 -0.0834 0.2749 1.0000
5.000 0.9866 0.00840 0.00287 -0.0827 0.2621 1.0000
5.250 1.0092 0.00872 0.00309 -0.0818 0.2391 1.0000
5.500 1.0315 0.00907 0.00332 -0.0809 0.2137 1.0000
5.750 1.0525 0.00952 0.00362 -0.0798 0.1805 1.0000
6.000 1.0655 0.01068 0.00430 -0.0774 0.0935 1.0000
6.250 1.0826 0.01150 0.00489 -0.0757 0.0501 1.0000
6.500 1.1010 0.01221 0.00545 -0.0741 0.0167 1.0000
6.750 1.1224 0.01265 0.00586 -0.0731 0.0109 1.0000
7.000 1.1443 0.01303 0.00625 -0.0721 0.0084 1.0000
7.250 1.1663 0.01339 0.00665 -0.0712 0.0071 1.0000
7.500 1.1876 0.01381 0.00710 -0.0702 0.0060 1.0000
7.750 1.2089 0.01421 0.00753 -0.0692 0.0052 1.0000
8.000 1.2290 0.01470 0.00806 -0.0680 0.0045 1.0000
8.250 1.2495 0.01512 0.00854 -0.0669 0.0041 1.0000
8.500 1.2691 0.01561 0.00908 -0.0656 0.0037 1.0000
8.750 1.2881 0.01612 0.00964 -0.0643 0.0034 1.0000
9.000 1.3044 0.01681 0.01039 -0.0625 0.0031 1.0000
9.250 1.3216 0.01739 0.01104 -0.0609 0.0030 1.0000
9.500 1.3379 0.01800 0.01173 -0.0592 0.0028 1.0000
9.750 1.3530 0.01859 0.01239 -0.0573 0.0026 1.0000
10.000 1.3649 0.01923 0.01310 -0.0547 0.0024 1.0000
10.250 1.3780 0.01978 0.01370 -0.0525 0.0023 1.0000
10.500 1.3860 0.02065 0.01464 -0.0496 0.0022 1.0000
10.750 1.3911 0.02172 0.01580 -0.0464 0.0021 1.0000
11.000 1.3998 0.02261 0.01679 -0.0440 0.0020 1.0000
11.250 1.4067 0.02366 0.01794 -0.0415 0.0019 1.0000
11.500 1.4100 0.02501 0.01940 -0.0387 0.0019 1.0000
11.750 1.4175 0.02614 0.02065 -0.0367 0.0017 1.0000
12.000 1.4221 0.02755 0.02216 -0.0346 0.0017 1.0000
12.250 1.4246 0.02921 0.02394 -0.0326 0.0016 1.0000
12.500 1.4218 0.03144 0.02631 -0.0304 0.0017 1.0000
12.750 1.4281 0.03299 0.02794 -0.0292 0.0015 1.0000
13.000 1.4249 0.03551 0.03060 -0.0277 0.0016 1.0000
13.250 1.4227 0.03806 0.03329 -0.0265 0.0016 1.0000
13.500 1.4253 0.04027 0.03559 -0.0258 0.0015 1.0000
13.750 1.4266 0.04268 0.03810 -0.0253 0.0014 1.0000
14.000 1.4253 0.04550 0.04104 -0.0249 0.0014 1.0000
14.250 1.4276 0.04803 0.04365 -0.0249 0.0013 1.0000
14.500 1.4115 0.05296 0.04878 -0.0250 0.0014 1.0000
14.750 1.4142 0.05574 0.05163 -0.0256 0.0013 1.0000
15.000 1.4071 0.05996 0.05598 -0.0265 0.0013 1.0000
15.250 1.3961 0.06485 0.06103 -0.0276 0.0013 1.0000
15.500 1.3889 0.06941 0.06570 -0.0289 0.0013 1.0000
15.750 1.3787 0.07454 0.07097 -0.0305 0.0013 1.0000
16.000 1.3674 0.08000 0.07656 -0.0325 0.0012 1.0000
16.250 1.3531 0.08617 0.08287 -0.0348 0.0012 1.0000
16.500 1.3363 0.09300 0.08985 -0.0376 0.0012 1.0000
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