EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER E850 AIRFOIL (e850-il) Reynolds number: 50,000 Max Cl/Cd: 23.07 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e850-il-50000.txt Download as CSV file: xf-e850-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E850 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
------ -------- --------- --------- -------- -------- --------
-6.500 -0.4470 0.07075 0.06492 -0.0102 1.0000 0.3188
-6.000 -0.5684 0.05847 0.05132 -0.0432 1.0000 0.1251
-5.750 -0.5508 0.05217 0.04453 -0.0441 1.0000 0.1001
-5.500 -0.5337 0.04797 0.04014 -0.0437 1.0000 0.0951
-5.250 -0.5121 0.04382 0.03513 -0.0440 1.0000 0.0847
-5.000 -0.4912 0.03999 0.03074 -0.0437 1.0000 0.0828
-4.750 -0.4676 0.03653 0.02678 -0.0432 1.0000 0.0799
-4.500 -0.4416 0.03339 0.02305 -0.0424 1.0000 0.0770
-4.250 -0.4148 0.03080 0.01990 -0.0413 1.0000 0.0754
-4.000 -0.3892 0.02844 0.01731 -0.0399 1.0000 0.0772
-3.750 -0.3643 0.02646 0.01517 -0.0379 1.0000 0.0832
-3.500 -0.3418 0.02453 0.01331 -0.0363 1.0000 0.1052
-3.250 -0.3160 0.02128 0.01073 -0.0359 1.0000 0.1929
-3.000 -0.3320 0.01982 0.01216 -0.0217 1.0000 0.7179
-2.750 -0.3478 0.02017 0.01268 -0.0078 1.0000 0.8016
-2.500 -0.3565 0.02005 0.01255 0.0038 1.0000 0.8704
-2.250 -0.2340 0.02085 0.01212 -0.0088 1.0000 0.9662
-2.000 -0.1483 0.02039 0.01080 -0.0219 1.0000 0.9926
-1.750 -0.1297 0.01977 0.00999 -0.0228 1.0000 1.0000
-1.500 -0.1350 0.01904 0.00923 -0.0193 1.0000 1.0000
-1.250 -0.1407 0.01829 0.00843 -0.0158 1.0000 1.0000
-1.000 -0.1327 0.01776 0.00775 -0.0146 1.0000 1.0000
-0.750 -0.1104 0.01755 0.00732 -0.0156 1.0000 1.0000
-0.500 -0.0840 0.01751 0.00706 -0.0169 1.0000 1.0000
-0.250 -0.0569 0.01757 0.00683 -0.0181 1.0000 1.0000
0.000 -0.0303 0.01768 0.00676 -0.0190 1.0000 1.0000
0.250 -0.0044 0.01783 0.00676 -0.0196 1.0000 1.0000
0.500 0.0209 0.01802 0.00683 -0.0200 1.0000 1.0000
0.750 0.0457 0.01824 0.00697 -0.0203 1.0000 1.0000
1.000 0.0699 0.01848 0.00715 -0.0205 1.0000 1.0000
1.250 0.0938 0.01875 0.00740 -0.0206 1.0000 1.0000
1.500 0.1172 0.01904 0.00770 -0.0205 1.0000 1.0000
1.750 0.1403 0.01937 0.00803 -0.0205 1.0000 1.0000
2.000 0.1630 0.01972 0.00843 -0.0204 1.0000 1.0000
2.250 0.1854 0.02011 0.00888 -0.0203 1.0000 1.0000
2.500 0.2073 0.02053 0.00939 -0.0201 1.0000 1.0000
2.750 0.2288 0.02099 0.00998 -0.0199 1.0000 1.0000
3.000 0.2499 0.02149 0.01063 -0.0197 1.0000 1.0000
3.250 0.2706 0.02205 0.01157 -0.0195 1.0000 1.0000
3.500 0.2907 0.02267 0.01244 -0.0193 1.0000 1.0000
3.750 0.3101 0.02336 0.01337 -0.0192 1.0000 1.0000
4.000 0.3288 0.02412 0.01440 -0.0190 1.0000 1.0000
4.250 0.3465 0.02498 0.01554 -0.0189 1.0000 1.0000
4.500 0.3632 0.02597 0.01685 -0.0188 1.0000 1.0000
4.750 0.6695 0.02902 0.01786 -0.0463 0.0993 1.0000
5.000 0.7122 0.03296 0.02189 -0.0473 0.0901 1.0000
5.250 0.7445 0.03670 0.02605 -0.0466 0.0891 1.0000
5.500 0.7703 0.04015 0.03003 -0.0451 0.0888 1.0000
5.750 0.7896 0.04315 0.03373 -0.0427 0.0868 1.0000
6.000 0.8068 0.04663 0.03776 -0.0405 0.0861 1.0000
6.250 0.8245 0.05113 0.04252 -0.0389 0.0887 1.0000
6.500 0.8384 0.05556 0.04768 -0.0363 0.1011 1.0000
6.750 0.8486 0.06075 0.05368 -0.0340 0.1255 1.0000
7.000 0.8026 0.05882 0.05298 -0.0289 0.1665 1.0000
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Polar data table (+)
Polar graphs
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