EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 50,000 Max Cl/Cd: 35.56 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e853-il-50000.txt Download as CSV file: xf-e853-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E853 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3603 0.10342 0.09689 -0.0287 1.0000 0.2949
-8.250 -0.3688 0.10148 0.09508 -0.0278 1.0000 0.3054
-8.000 -0.3800 0.09999 0.09374 -0.0262 1.0000 0.3178
-7.750 -0.3761 0.09716 0.09097 -0.0245 1.0000 0.3306
-7.500 -0.3859 0.09553 0.08947 -0.0220 1.0000 0.3451
-7.250 -0.3672 0.09110 0.08505 -0.0206 1.0000 0.3558
-7.000 -0.3795 0.08912 0.08322 -0.0184 1.0000 0.3611
-6.500 -0.4704 0.06772 0.06287 -0.0310 1.0000 0.1608
-6.250 -0.5275 0.06408 0.05838 -0.0469 1.0000 0.1340
-6.000 -0.5259 0.05770 0.05160 -0.0503 1.0000 0.1190
-5.750 -0.5149 0.05175 0.04496 -0.0535 1.0000 0.1076
-5.500 -0.4982 0.04692 0.03963 -0.0550 1.0000 0.1018
-5.250 -0.4733 0.04272 0.03427 -0.0568 1.0000 0.0965
-5.000 -0.4496 0.03937 0.03042 -0.0571 1.0000 0.0964
-4.750 -0.4284 0.03661 0.02755 -0.0571 1.0000 0.1034
-4.500 -0.4020 0.03423 0.02449 -0.0572 1.0000 0.1111
-4.250 -0.3788 0.03200 0.02219 -0.0564 1.0000 0.1204
-4.000 -0.3560 0.03018 0.02030 -0.0557 1.0000 0.1406
-3.750 -0.3334 0.02845 0.01860 -0.0545 1.0000 0.1665
-3.500 -0.3103 0.02651 0.01702 -0.0539 1.0000 0.2198
-3.250 -0.2931 0.02501 0.01779 -0.0505 1.0000 0.5344
-3.000 -0.2922 0.02625 0.01909 -0.0429 1.0000 0.6232
-2.750 -0.2915 0.02695 0.01981 -0.0357 1.0000 0.6713
-2.500 -0.2889 0.02732 0.02011 -0.0295 1.0000 0.7122
-2.250 -0.2847 0.02746 0.02009 -0.0240 1.0000 0.7498
-2.000 -0.2829 0.02743 0.01999 -0.0180 1.0000 0.7849
-1.750 -0.2808 0.02725 0.01973 -0.0124 1.0000 0.8209
-1.500 -0.2784 0.02693 0.01932 -0.0070 1.0000 0.8572
-1.250 -0.2721 0.02652 0.01883 -0.0028 1.0000 0.8930
-1.000 -0.2505 0.02626 0.01841 -0.0023 1.0000 0.9294
-0.750 -0.2005 0.02638 0.01825 -0.0085 1.0000 0.9636
-0.500 -0.1612 0.02623 0.01783 -0.0139 1.0000 1.0000
-0.250 -0.1402 0.02613 0.01751 -0.0163 1.0000 1.0000
0.000 -0.1105 0.02639 0.01753 -0.0202 1.0000 1.0000
0.250 -0.0779 0.02687 0.01776 -0.0243 1.0000 1.0000
0.500 -0.0451 0.02748 0.01809 -0.0283 1.0000 1.0000
0.750 -0.0136 0.02817 0.01856 -0.0318 1.0000 1.0000
1.000 0.0158 0.02892 0.01910 -0.0346 1.0000 1.0000
1.250 0.0431 0.02971 0.01971 -0.0369 1.0000 1.0000
1.500 0.0686 0.03054 0.02034 -0.0387 1.0000 1.0000
1.750 0.1047 0.03187 0.02150 -0.0424 0.9947 1.0000
2.000 0.1405 0.03315 0.02266 -0.0460 0.9868 1.0000
2.250 0.1771 0.03455 0.02395 -0.0496 0.9785 1.0000
2.500 0.2167 0.03612 0.02543 -0.0536 0.9699 1.0000
2.750 0.2411 0.03705 0.02632 -0.0550 0.9626 1.0000
3.000 0.2742 0.03839 0.02763 -0.0577 0.9535 1.0000
3.250 0.3112 0.03989 0.02913 -0.0611 0.9436 1.0000
3.500 0.3351 0.04094 0.03019 -0.0623 0.9344 1.0000
3.750 0.3639 0.04222 0.03149 -0.0642 0.9238 1.0000
4.000 0.3948 0.04356 0.03288 -0.0664 0.9120 1.0000
4.250 0.4260 0.04491 0.03435 -0.0685 0.8993 1.0000
4.500 0.4567 0.04624 0.03576 -0.0705 0.8856 1.0000
4.750 0.4867 0.04756 0.03719 -0.0722 0.8710 1.0000
5.000 0.5171 0.04887 0.03862 -0.0739 0.8553 1.0000
5.250 0.5524 0.05017 0.04012 -0.0761 0.8382 1.0000
5.500 0.5893 0.05140 0.04154 -0.0782 0.8196 1.0000
5.750 0.6158 0.05249 0.04281 -0.0788 0.7996 1.0000
6.000 0.6590 0.05336 0.04394 -0.0810 0.7783 1.0000
6.250 0.6929 0.05406 0.04495 -0.0818 0.7551 1.0000
6.500 0.7286 0.05446 0.04564 -0.0823 0.7299 1.0000
6.750 0.7773 0.05386 0.04543 -0.0829 0.7015 1.0000
7.000 0.8536 0.05042 0.04268 -0.0836 0.6679 1.0000
7.250 0.9699 0.04027 0.03357 -0.0819 0.6233 1.0000
7.500 1.0472 0.02945 0.02342 -0.0738 0.5162 1.0000
7.750 1.0385 0.02953 0.02167 -0.0637 0.3232 1.0000
8.000 1.0304 0.03282 0.02395 -0.0587 0.2441 1.0000
8.250 1.0410 0.03587 0.02638 -0.0561 0.1849 1.0000
8.500 1.0960 0.03996 0.03001 -0.0588 0.1302 1.0000
8.750 1.1447 0.04446 0.03452 -0.0609 0.1052 1.0000
9.000 1.1760 0.04881 0.03908 -0.0609 0.0935 1.0000
9.250 1.1923 0.05262 0.04344 -0.0589 0.0876 1.0000
9.500 1.2076 0.05689 0.04786 -0.0578 0.0813 1.0000
9.750 1.2083 0.06060 0.05216 -0.0545 0.0794 1.0000
10.000 1.2083 0.06489 0.05693 -0.0516 0.0792 1.0000
10.250 1.2034 0.06925 0.06169 -0.0486 0.0796 1.0000
10.500 1.1947 0.07355 0.06634 -0.0457 0.0802 1.0000
10.750 1.1833 0.07781 0.07087 -0.0429 0.0810 1.0000
11.000 1.1723 0.08235 0.07562 -0.0407 0.0817 1.0000
11.250 1.1661 0.08761 0.08102 -0.0393 0.0825 1.0000
11.500 1.1216 0.09008 0.08390 -0.0366 0.0843 1.0000
11.750 1.0757 0.09534 0.08946 -0.0374 0.0862 1.0000
12.000 1.0357 0.10246 0.09675 -0.0407 0.0886 1.0000
12.250 1.0054 0.11052 0.10490 -0.0452 0.0910 1.0000
12.500 0.9884 0.11837 0.11276 -0.0491 0.0934 1.0000
12.750 0.9902 0.12480 0.11920 -0.0505 0.0953 1.0000
13.000 0.9549 0.13948 0.13389 -0.0615 0.1093 1.0000
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Polar data table (+)
Polar graphs
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