EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 500,000 Max Cl/Cd: 120.78 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e853-il-500000.txt Download as CSV file: xf-e853-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4135 0.08758 0.08547 -0.0450 1.0000 0.0160
-9.000 -0.4209 0.08366 0.08161 -0.0456 1.0000 0.0163
-8.750 -0.4310 0.07983 0.07783 -0.0459 1.0000 0.0165
-7.000 -0.3601 0.02182 0.01713 -0.1007 0.9533 0.0085
-6.750 -0.3287 0.02050 0.01561 -0.1018 0.9481 0.0081
-6.500 -0.2955 0.01813 0.01298 -0.1036 0.9449 0.0078
-6.250 -0.2666 0.01593 0.01052 -0.1044 0.9375 0.0078
-6.000 -0.2301 0.01432 0.00871 -0.1066 0.9331 0.0079
-5.750 -0.1966 0.01238 0.00653 -0.1085 0.9260 0.0085
-5.500 -0.1593 0.01133 0.00538 -0.1110 0.9189 0.0109
-5.250 -0.1248 0.01048 0.00440 -0.1126 0.9087 0.0168
-5.000 -0.0913 0.00984 0.00380 -0.1142 0.8978 0.0399
-4.750 -0.0599 0.00940 0.00340 -0.1153 0.8863 0.0667
-4.500 -0.0308 0.00883 0.00300 -0.1160 0.8743 0.1273
-4.250 -0.0034 0.00802 0.00257 -0.1168 0.8626 0.2508
-4.000 0.0230 0.00743 0.00238 -0.1171 0.8510 0.3844
-3.750 0.0508 0.00733 0.00231 -0.1171 0.8406 0.4316
-3.500 0.0788 0.00732 0.00224 -0.1172 0.8310 0.4578
-3.250 0.1069 0.00734 0.00219 -0.1172 0.8220 0.4792
-3.000 0.1345 0.00737 0.00216 -0.1171 0.8129 0.4999
-2.750 0.1626 0.00741 0.00212 -0.1172 0.8052 0.5131
-2.500 0.1904 0.00743 0.00209 -0.1172 0.7971 0.5239
-2.250 0.2182 0.00746 0.00207 -0.1172 0.7898 0.5347
-2.000 0.2460 0.00750 0.00207 -0.1172 0.7827 0.5481
-1.750 0.2738 0.00754 0.00208 -0.1172 0.7761 0.5602
-1.500 0.3017 0.00757 0.00206 -0.1172 0.7695 0.5695
-1.250 0.3297 0.00760 0.00205 -0.1173 0.7635 0.5768
-1.000 0.3576 0.00761 0.00204 -0.1173 0.7572 0.5836
-0.750 0.3859 0.00765 0.00204 -0.1175 0.7520 0.5902
-0.500 0.4136 0.00765 0.00205 -0.1175 0.7459 0.5970
-0.250 0.4417 0.00768 0.00207 -0.1176 0.7407 0.6037
0.000 0.4697 0.00772 0.00210 -0.1177 0.7356 0.6109
0.250 0.4975 0.00773 0.00214 -0.1178 0.7301 0.6182
0.500 0.5258 0.00778 0.00217 -0.1179 0.7254 0.6259
0.750 0.5535 0.00781 0.00224 -0.1180 0.7203 0.6341
1.000 0.5813 0.00783 0.00230 -0.1180 0.7151 0.6423
1.250 0.6097 0.00790 0.00236 -0.1182 0.7107 0.6518
1.500 0.6369 0.00791 0.00244 -0.1181 0.7051 0.6613
1.750 0.6645 0.00794 0.00252 -0.1181 0.6994 0.6714
2.000 0.6917 0.00797 0.00261 -0.1180 0.6927 0.6827
2.250 0.7187 0.00799 0.00267 -0.1178 0.6857 0.6949
2.500 0.7454 0.00801 0.00277 -0.1176 0.6777 0.7083
2.750 0.7720 0.00804 0.00284 -0.1173 0.6692 0.7231
3.000 0.7974 0.00802 0.00291 -0.1168 0.6584 0.7394
3.250 0.8228 0.00801 0.00299 -0.1162 0.6469 0.7579
3.500 0.8485 0.00803 0.00310 -0.1157 0.6375 0.7791
4.000 0.8975 0.00803 0.00335 -0.1142 0.6164 0.8336
4.250 0.9193 0.00800 0.00347 -0.1128 0.6038 0.8725
4.500 0.9378 0.00789 0.00352 -0.1104 0.5898 0.9509
4.750 0.9650 0.00799 0.00361 -0.1104 0.5656 1.0000
5.000 0.9881 0.00822 0.00377 -0.1095 0.5336 1.0000
5.250 1.0092 0.00857 0.00398 -0.1082 0.4886 1.0000
5.500 1.0232 0.00938 0.00438 -0.1058 0.4010 1.0000
5.750 1.0324 0.01066 0.00508 -0.1027 0.2931 1.0000
6.000 1.0435 0.01186 0.00579 -0.1001 0.2027 1.0000
6.250 1.0573 0.01286 0.00644 -0.0980 0.1382 1.0000
6.500 1.0731 0.01370 0.00705 -0.0961 0.0970 1.0000
6.750 1.0895 0.01447 0.00764 -0.0943 0.0665 1.0000
7.000 1.1059 0.01521 0.00828 -0.0926 0.0446 1.0000
7.250 1.1231 0.01586 0.00886 -0.0909 0.0302 1.0000
7.500 1.1384 0.01656 0.00952 -0.0889 0.0204 1.0000
7.750 1.1491 0.01749 0.01044 -0.0859 0.0118 1.0000
8.000 1.1561 0.01872 0.01176 -0.0823 0.0083 1.0000
8.250 1.1682 0.01960 0.01272 -0.0798 0.0071 1.0000
8.500 1.1794 0.02057 0.01377 -0.0772 0.0064 1.0000
8.750 1.1878 0.02176 0.01505 -0.0743 0.0059 1.0000
9.000 1.1933 0.02323 0.01663 -0.0712 0.0056 1.0000
9.250 1.1969 0.02506 0.01861 -0.0679 0.0054 1.0000
9.500 1.2043 0.02683 0.02051 -0.0654 0.0054 1.0000
9.750 1.2136 0.02878 0.02261 -0.0632 0.0053 1.0000
10.000 1.2252 0.03082 0.02484 -0.0613 0.0053 1.0000
10.250 1.2379 0.03304 0.02725 -0.0597 0.0053 1.0000
10.500 1.2498 0.03498 0.02936 -0.0581 0.0054 1.0000
10.750 1.2598 0.03712 0.03169 -0.0563 0.0054 1.0000
11.000 1.2676 0.03927 0.03404 -0.0545 0.0055 1.0000
11.250 1.2725 0.04177 0.03679 -0.0525 0.0057 1.0000
11.500 1.2533 0.05041 0.04629 -0.0483 0.0070 1.0000
11.750 1.2337 0.05578 0.05202 -0.0457 0.0074 1.0000
12.000 1.2152 0.06060 0.05710 -0.0440 0.0076 1.0000
12.250 1.1935 0.06595 0.06269 -0.0432 0.0079 1.0000
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Polar data table (+)
Polar graphs
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