E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 500,000 Max Cl/Cd: 110.83 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e174-il-500000-n5.txt Download as CSV file: xf-e174-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E174 (Dicke 8.92%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3440 0.09221 0.09001 -0.0291 1.0000 0.0065
-8.500 -0.3423 0.08856 0.08639 -0.0305 1.0000 0.0062
-8.250 -0.3418 0.08485 0.08272 -0.0318 1.0000 0.0059
-8.000 -0.3270 0.07870 0.07657 -0.0392 0.9601 0.0056
-7.750 -0.3065 0.07082 0.06860 -0.0504 0.9098 0.0054
-7.500 -0.3062 0.06669 0.06432 -0.0538 0.8635 0.0054
-7.250 -0.3082 0.06070 0.05820 -0.0592 0.8329 0.0053
-7.000 -0.3011 0.05577 0.05315 -0.0643 0.8116 0.0054
-6.750 -0.2903 0.05024 0.04747 -0.0696 0.7943 0.0056
-6.500 -0.2799 0.04101 0.03796 -0.0763 0.7806 0.0056
-6.250 -0.2734 0.02595 0.02202 -0.0813 0.7705 0.0058
-6.000 -0.2538 0.02105 0.01642 -0.0819 0.7596 0.0061
-5.750 -0.2296 0.01898 0.01395 -0.0819 0.7490 0.0065
-5.500 -0.2043 0.01747 0.01207 -0.0819 0.7392 0.0071
-5.250 -0.1788 0.01588 0.01009 -0.0817 0.7302 0.0073
-5.000 -0.1526 0.01454 0.00844 -0.0815 0.7210 0.0075
-4.750 -0.1260 0.01356 0.00720 -0.0813 0.7128 0.0077
-4.500 -0.0993 0.01273 0.00616 -0.0811 0.7046 0.0079
-4.250 -0.0728 0.01172 0.00498 -0.0809 0.6971 0.0087
-4.000 -0.0456 0.01127 0.00442 -0.0808 0.6897 0.0095
-3.750 -0.0181 0.01088 0.00394 -0.0807 0.6827 0.0104
-3.500 0.0095 0.01055 0.00349 -0.0806 0.6758 0.0115
-3.250 0.0371 0.01019 0.00305 -0.0806 0.6692 0.0137
-3.000 0.0649 0.00993 0.00273 -0.0805 0.6628 0.0162
-2.750 0.0928 0.00970 0.00241 -0.0805 0.6569 0.0191
-2.500 0.1206 0.00946 0.00216 -0.0805 0.6506 0.0281
-2.250 0.1484 0.00927 0.00197 -0.0805 0.6450 0.0423
-2.000 0.1764 0.00911 0.00182 -0.0805 0.6393 0.0587
-1.750 0.2041 0.00893 0.00170 -0.0805 0.6336 0.0891
-1.500 0.2319 0.00871 0.00159 -0.0806 0.6282 0.1332
-1.250 0.2597 0.00851 0.00151 -0.0807 0.6227 0.1810
-1.000 0.2873 0.00832 0.00145 -0.0807 0.6177 0.2419
-0.750 0.3151 0.00813 0.00141 -0.0808 0.6122 0.3030
-0.500 0.3425 0.00788 0.00138 -0.0809 0.6070 0.3922
-0.250 0.3696 0.00760 0.00139 -0.0809 0.6022 0.5020
0.000 0.3964 0.00731 0.00141 -0.0808 0.5967 0.6132
0.250 0.4215 0.00701 0.00145 -0.0802 0.5917 0.7354
0.500 0.4422 0.00665 0.00149 -0.0782 0.5870 0.8817
0.750 0.4808 0.00654 0.00144 -0.0803 0.5813 1.0000
1.000 0.5085 0.00663 0.00145 -0.0802 0.5764 1.0000
1.250 0.5364 0.00669 0.00148 -0.0803 0.5710 1.0000
1.500 0.5642 0.00676 0.00151 -0.0802 0.5654 1.0000
1.750 0.5919 0.00685 0.00155 -0.0802 0.5602 1.0000
2.000 0.6197 0.00692 0.00160 -0.0802 0.5540 1.0000
2.250 0.6472 0.00702 0.00166 -0.0801 0.5477 1.0000
2.500 0.6750 0.00709 0.00172 -0.0801 0.5400 1.0000
2.750 0.7024 0.00720 0.00179 -0.0800 0.5319 1.0000
3.000 0.7298 0.00730 0.00186 -0.0800 0.5226 1.0000
3.250 0.7573 0.00740 0.00197 -0.0799 0.5133 1.0000
3.500 0.7845 0.00752 0.00206 -0.0798 0.5038 1.0000
3.750 0.8117 0.00765 0.00217 -0.0797 0.4934 1.0000
4.000 0.8388 0.00778 0.00229 -0.0796 0.4814 1.0000
4.250 0.8657 0.00792 0.00244 -0.0795 0.4687 1.0000
4.500 0.8924 0.00809 0.00258 -0.0794 0.4545 1.0000
4.750 0.9188 0.00829 0.00275 -0.0792 0.4378 1.0000
5.000 0.9448 0.00853 0.00293 -0.0789 0.4152 1.0000
5.250 0.9702 0.00882 0.00317 -0.0786 0.3887 1.0000
5.500 0.9946 0.00924 0.00345 -0.0782 0.3526 1.0000
5.750 1.0176 0.00982 0.00383 -0.0776 0.3050 1.0000
6.000 1.0397 0.01049 0.00428 -0.0770 0.2576 1.0000
6.250 1.0620 0.01113 0.00477 -0.0764 0.2173 1.0000
6.500 1.0833 0.01188 0.00530 -0.0756 0.1734 1.0000
6.750 1.1033 0.01273 0.00590 -0.0747 0.1265 1.0000
7.000 1.1240 0.01347 0.00648 -0.0739 0.0942 1.0000
7.250 1.1450 0.01415 0.00704 -0.0731 0.0700 1.0000
7.500 1.1655 0.01485 0.00764 -0.0723 0.0498 1.0000
7.750 1.1860 0.01552 0.00827 -0.0714 0.0347 1.0000
8.000 1.2060 0.01620 0.00891 -0.0704 0.0231 1.0000
8.250 1.2251 0.01693 0.00962 -0.0693 0.0151 1.0000
8.500 1.2443 0.01762 0.01033 -0.0682 0.0110 1.0000
8.750 1.2619 0.01843 0.01116 -0.0669 0.0082 1.0000
9.000 1.2804 0.01908 0.01189 -0.0657 0.0072 1.0000
9.250 1.2971 0.01984 0.01272 -0.0643 0.0062 1.0000
9.500 1.3105 0.02079 0.01378 -0.0625 0.0054 1.0000
9.750 1.3221 0.02172 0.01480 -0.0603 0.0050 1.0000
10.000 1.3320 0.02258 0.01577 -0.0579 0.0047 1.0000
10.250 1.3404 0.02357 0.01686 -0.0555 0.0045 1.0000
10.500 1.3476 0.02470 0.01809 -0.0532 0.0042 1.0000
10.750 1.3537 0.02598 0.01948 -0.0510 0.0041 1.0000
11.000 1.3601 0.02734 0.02094 -0.0491 0.0039 1.0000
11.250 1.3651 0.02890 0.02260 -0.0474 0.0037 1.0000
11.500 1.3697 0.03060 0.02441 -0.0459 0.0036 1.0000
11.750 1.3727 0.03255 0.02646 -0.0446 0.0034 1.0000
12.000 1.3747 0.03470 0.02872 -0.0434 0.0033 1.0000
12.250 1.3718 0.03748 0.03165 -0.0423 0.0031 1.0000
12.500 1.3689 0.04039 0.03470 -0.0415 0.0030 1.0000
12.750 1.3764 0.04226 0.03668 -0.0411 0.0029 1.0000
13.000 1.3748 0.04523 0.03980 -0.0406 0.0029 1.0000
13.250 1.3767 0.04786 0.04256 -0.0404 0.0028 1.0000
13.500 1.3805 0.05033 0.04516 -0.0404 0.0027 1.0000
13.750 1.3768 0.05382 0.04881 -0.0405 0.0026 1.0000
14.000 1.3751 0.05715 0.05228 -0.0408 0.0025 1.0000
14.250 1.3694 0.06115 0.05643 -0.0413 0.0025 1.0000
14.500 1.3674 0.06478 0.06020 -0.0421 0.0024 1.0000
14.750 1.3603 0.06931 0.06490 -0.0432 0.0024 1.0000
15.000 1.3544 0.07387 0.06962 -0.0445 0.0024 1.0000
15.250 1.3471 0.07882 0.07473 -0.0462 0.0023 1.0000
15.500 1.3386 0.08420 0.08027 -0.0482 0.0023 1.0000
15.750 1.3284 0.09009 0.08634 -0.0506 0.0023 1.0000
16.000 1.3189 0.09610 0.09250 -0.0533 0.0023 1.0000
16.250 1.3078 0.10265 0.09922 -0.0565 0.0023 1.0000
16.500 1.2950 0.10978 0.10651 -0.0601 0.0023 1.0000
16.750 1.2817 0.11730 0.11419 -0.0640 0.0023 1.0000
17.000 1.2685 0.12508 0.12214 -0.0684 0.0023 1.0000
17.250 1.2542 0.13345 0.13066 -0.0732 0.0023 1.0000
17.500 1.2399 0.14210 0.13947 -0.0783 0.0023 1.0000
17.750 1.2245 0.15136 0.14888 -0.0839 0.0023 1.0000
18.000 1.2083 0.16124 0.15891 -0.0899 0.0023 1.0000
18.250 1.1925 0.17150 0.16930 -0.0962 0.0023 1.0000
18.500 1.1746 0.18288 0.18080 -0.1030 0.0024 1.0000
18.750 1.1515 0.19711 0.19515 -0.1113 0.0025 1.0000
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Polar data table (+)
Polar graphs
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