EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 50,000 Max Cl/Cd: 35.91 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e853-il-50000-n5.txt Download as CSV file: xf-e853-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3981 0.10171 0.09477 -0.0478 1.0000 0.0370
-9.500 -0.4020 0.09764 0.09079 -0.0489 1.0000 0.0371
-9.250 -0.4075 0.09336 0.08662 -0.0502 1.0000 0.0364
-8.750 -0.4467 0.07908 0.07252 -0.0584 1.0000 0.0321
-8.500 -0.4600 0.07576 0.06929 -0.0584 1.0000 0.0318
-8.250 -0.4778 0.07267 0.06629 -0.0580 1.0000 0.0316
-8.000 -0.4941 0.06922 0.06289 -0.0583 1.0000 0.0314
-7.750 -0.5075 0.06611 0.05975 -0.0577 1.0000 0.0311
-7.500 -0.5212 0.06268 0.05622 -0.0572 1.0000 0.0312
-7.250 -0.5295 0.05942 0.05282 -0.0565 1.0000 0.0311
-7.000 -0.5343 0.05599 0.04914 -0.0561 1.0000 0.0313
-6.750 -0.5341 0.05251 0.04526 -0.0559 1.0000 0.0318
-6.500 -0.5296 0.04893 0.04137 -0.0558 1.0000 0.0327
-6.250 -0.5129 0.04588 0.03814 -0.0573 0.9973 0.0349
-6.000 -0.4826 0.04228 0.03405 -0.0606 0.9914 0.0371
-5.750 -0.4507 0.03872 0.02989 -0.0631 0.9856 0.0386
-5.500 -0.4176 0.03571 0.02630 -0.0648 0.9805 0.0411
-5.250 -0.3869 0.03350 0.02376 -0.0661 0.9744 0.0472
-5.000 -0.3535 0.03173 0.02160 -0.0672 0.9696 0.0549
-4.750 -0.3259 0.03017 0.01995 -0.0676 0.9628 0.0653
-4.500 -0.2931 0.02863 0.01822 -0.0689 0.9576 0.0821
-4.000 -0.2305 0.02516 0.01518 -0.0731 0.9456 0.1736
-3.750 -0.2034 0.02361 0.01501 -0.0744 0.9392 0.4113
-3.500 -0.1736 0.02400 0.01533 -0.0742 0.9325 0.5156
-3.250 -0.1490 0.02437 0.01548 -0.0731 0.9248 0.5663
-3.000 -0.1216 0.02473 0.01571 -0.0722 0.9186 0.6090
-2.750 -0.1003 0.02499 0.01586 -0.0702 0.9109 0.6397
-2.500 -0.0709 0.02507 0.01574 -0.0702 0.9053 0.6650
-2.250 -0.0457 0.02509 0.01556 -0.0697 0.8983 0.6809
-2.000 -0.0147 0.02503 0.01525 -0.0705 0.8925 0.6950
-1.750 0.0142 0.02501 0.01503 -0.0711 0.8865 0.7081
-1.500 0.0431 0.02499 0.01484 -0.0717 0.8803 0.7208
-1.250 0.0779 0.02492 0.01460 -0.0732 0.8761 0.7333
-1.000 0.0993 0.02500 0.01457 -0.0725 0.8682 0.7451
-0.750 0.1321 0.02497 0.01442 -0.0737 0.8638 0.7581
-0.500 0.1551 0.02507 0.01446 -0.0732 0.8567 0.7712
-0.250 0.1848 0.02508 0.01440 -0.0739 0.8515 0.7854
0.000 0.2115 0.02514 0.01441 -0.0740 0.8460 0.8008
0.250 0.2359 0.02524 0.01450 -0.0737 0.8395 0.8178
0.500 0.2676 0.02519 0.01445 -0.0745 0.8356 0.8362
0.750 0.2847 0.02541 0.01471 -0.0730 0.8277 0.8592
1.000 0.3167 0.02538 0.01472 -0.0739 0.8232 0.8874
1.250 0.3489 0.02554 0.01494 -0.0755 0.8171 0.9324
1.500 0.3866 0.02572 0.01510 -0.0785 0.8112 1.0000
1.750 0.4275 0.02591 0.01525 -0.0817 0.8077 1.0000
2.000 0.4476 0.02654 0.01583 -0.0817 0.7992 1.0000
2.250 0.4849 0.02680 0.01606 -0.0840 0.7950 1.0000
2.500 0.5057 0.02744 0.01669 -0.0838 0.7869 1.0000
2.750 0.5402 0.02775 0.01706 -0.0855 0.7820 1.0000
3.000 0.5620 0.02838 0.01771 -0.0853 0.7741 1.0000
3.250 0.5948 0.02871 0.01811 -0.0865 0.7686 1.0000
3.500 0.6165 0.02934 0.01880 -0.0861 0.7603 1.0000
3.750 0.6500 0.02961 0.01923 -0.0873 0.7545 1.0000
4.000 0.6701 0.03027 0.01998 -0.0866 0.7452 1.0000
4.250 0.7076 0.03035 0.02023 -0.0880 0.7396 1.0000
4.500 0.7265 0.03101 0.02102 -0.0870 0.7291 1.0000
4.750 0.7528 0.03139 0.02162 -0.0869 0.7199 1.0000
5.000 0.7897 0.03129 0.02174 -0.0878 0.7121 1.0000
5.250 0.8130 0.03161 0.02227 -0.0869 0.7001 1.0000
5.500 0.8405 0.03162 0.02250 -0.0863 0.6873 1.0000
5.750 0.8732 0.03116 0.02231 -0.0858 0.6728 1.0000
6.000 0.9114 0.03008 0.02159 -0.0854 0.6550 1.0000
6.250 0.9354 0.02947 0.02123 -0.0832 0.6314 1.0000
6.500 0.9582 0.02880 0.02080 -0.0807 0.6044 1.0000
6.750 0.9781 0.02823 0.02044 -0.0778 0.5727 1.0000
7.000 0.9872 0.02823 0.02064 -0.0740 0.5335 1.0000
7.250 0.9973 0.02817 0.02064 -0.0700 0.4756 1.0000
7.500 1.0119 0.02818 0.01994 -0.0660 0.3544 1.0000
7.750 1.0069 0.03015 0.02118 -0.0616 0.2656 1.0000
8.000 1.0005 0.03256 0.02308 -0.0580 0.2056 1.0000
8.250 0.9971 0.03501 0.02528 -0.0551 0.1634 1.0000
8.500 0.9971 0.03743 0.02745 -0.0528 0.1342 1.0000
8.750 0.9999 0.03975 0.02963 -0.0508 0.1101 1.0000
9.000 1.0062 0.04199 0.03182 -0.0489 0.0937 1.0000
9.250 1.0164 0.04412 0.03399 -0.0473 0.0787 1.0000
9.500 1.0292 0.04617 0.03609 -0.0459 0.0656 1.0000
9.750 1.0526 0.04816 0.03815 -0.0447 0.0552 1.0000
10.000 1.0690 0.05025 0.04033 -0.0438 0.0467 1.0000
10.250 1.1087 0.05317 0.04369 -0.0433 0.0399 1.0000
10.500 1.1190 0.05571 0.04636 -0.0423 0.0358 1.0000
10.750 1.1313 0.05918 0.05013 -0.0413 0.0328 1.0000
11.000 1.1386 0.06314 0.05460 -0.0399 0.0314 1.0000
11.250 1.1375 0.06722 0.05910 -0.0385 0.0306 1.0000
11.500 1.1304 0.07146 0.06372 -0.0372 0.0300 1.0000
11.750 1.1192 0.07590 0.06850 -0.0365 0.0297 1.0000
12.000 1.1048 0.08067 0.07356 -0.0363 0.0295 1.0000
12.250 1.0878 0.08586 0.07904 -0.0368 0.0293 1.0000
12.500 1.0690 0.09159 0.08502 -0.0383 0.0295 1.0000
12.750 1.0486 0.09793 0.09158 -0.0406 0.0297 1.0000
13.000 1.0276 0.10495 0.09880 -0.0440 0.0301 1.0000
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Polar data table (+)
Polar graphs
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