EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 100,000 Max Cl/Cd: 60.59 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e853-il-100000.txt Download as CSV file: xf-e853-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3852 0.10212 0.09740 -0.0426 1.0000 0.1041
-9.000 -0.4054 0.09923 0.09466 -0.0455 1.0000 0.1094
-8.750 -0.4339 0.09648 0.09208 -0.0485 1.0000 0.1102
-8.500 -0.4024 0.09260 0.08815 -0.0434 1.0000 0.1146
-8.250 -0.4059 0.09003 0.08565 -0.0424 1.0000 0.1189
-8.000 -0.4370 0.08784 0.08366 -0.0429 1.0000 0.1227
-7.750 -0.4678 0.08616 0.08215 -0.0413 1.0000 0.1232
-7.500 -0.5072 0.08280 0.07892 -0.0443 1.0000 0.1237
-7.250 -0.4796 0.08153 0.07768 -0.0347 1.0000 0.1286
-7.000 -0.4949 0.07960 0.07584 -0.0328 1.0000 0.1311
-5.750 -0.4873 0.04317 0.03715 -0.0602 0.9904 0.0552
-5.500 -0.4532 0.03739 0.03082 -0.0637 0.9862 0.0496
-5.250 -0.4108 0.03279 0.02513 -0.0667 0.9828 0.0456
-5.000 -0.3767 0.02991 0.02178 -0.0683 0.9777 0.0465
-4.750 -0.3400 0.02810 0.01975 -0.0704 0.9728 0.0528
-4.500 -0.3013 0.02592 0.01739 -0.0724 0.9692 0.0615
-4.250 -0.2700 0.02441 0.01587 -0.0734 0.9630 0.0785
-4.000 -0.2327 0.02276 0.01438 -0.0756 0.9588 0.1129
-3.750 -0.1968 0.01993 0.01280 -0.0789 0.9551 0.2835
-3.500 -0.1684 0.02014 0.01370 -0.0787 0.9480 0.5285
-3.250 -0.1369 0.02081 0.01422 -0.0787 0.9420 0.5814
-3.000 -0.1116 0.02126 0.01464 -0.0776 0.9348 0.6129
-2.750 -0.0781 0.02161 0.01488 -0.0782 0.9301 0.6407
-2.500 -0.0562 0.02186 0.01506 -0.0769 0.9222 0.6632
-2.250 -0.0241 0.02211 0.01526 -0.0770 0.9178 0.6880
-2.000 -0.0051 0.02232 0.01538 -0.0754 0.9101 0.7078
-1.750 0.0277 0.02235 0.01533 -0.0762 0.9054 0.7239
-1.500 0.0522 0.02245 0.01533 -0.0760 0.8989 0.7367
-1.250 0.0833 0.02247 0.01525 -0.0771 0.8934 0.7491
-1.000 0.1219 0.02240 0.01506 -0.0793 0.8900 0.7611
-0.750 0.1373 0.02263 0.01527 -0.0776 0.8819 0.7717
-0.500 0.1722 0.02259 0.01518 -0.0792 0.8778 0.7838
-0.250 0.1924 0.02281 0.01538 -0.0784 0.8710 0.7958
0.000 0.2220 0.02287 0.01539 -0.0790 0.8659 0.8092
0.250 0.2594 0.02278 0.01529 -0.0809 0.8627 0.8234
0.500 0.2697 0.02321 0.01575 -0.0785 0.8542 0.8389
0.750 0.3037 0.02316 0.01571 -0.0796 0.8504 0.8568
1.000 0.3162 0.02353 0.01613 -0.0774 0.8429 0.8777
1.250 0.3437 0.02351 0.01617 -0.0774 0.8380 0.9047
1.500 0.3898 0.02328 0.01603 -0.0808 0.8353 0.9442
1.750 0.4203 0.02391 0.01668 -0.0838 0.8266 1.0000
2.000 0.4696 0.02395 0.01668 -0.0887 0.8232 1.0000
2.250 0.4944 0.02467 0.01735 -0.0899 0.8153 1.0000
2.500 0.5352 0.02480 0.01747 -0.0928 0.8105 1.0000
2.750 0.5860 0.02458 0.01731 -0.0969 0.8079 1.0000
3.000 0.5977 0.02554 0.01827 -0.0952 0.7974 1.0000
3.250 0.6494 0.02519 0.01799 -0.0991 0.7944 1.0000
3.500 0.6631 0.02602 0.01889 -0.0975 0.7838 1.0000
3.750 0.7165 0.02544 0.01842 -0.1011 0.7805 1.0000
4.000 0.7335 0.02613 0.01918 -0.0998 0.7696 1.0000
4.250 0.7637 0.02624 0.01941 -0.1000 0.7606 1.0000
4.500 0.8176 0.02510 0.01847 -0.1028 0.7541 1.0000
4.750 0.8532 0.02453 0.01805 -0.1030 0.7420 1.0000
5.000 0.8995 0.02312 0.01680 -0.1039 0.7284 1.0000
5.250 0.9436 0.02175 0.01557 -0.1044 0.7131 1.0000
5.500 0.9823 0.02072 0.01473 -0.1044 0.6969 1.0000
5.750 1.0066 0.02026 0.01444 -0.1025 0.6762 1.0000
6.000 1.0371 0.01935 0.01366 -0.1012 0.6521 1.0000
6.250 1.0602 0.01865 0.01308 -0.0987 0.6204 1.0000
6.500 1.0777 0.01811 0.01262 -0.0953 0.5764 1.0000
6.750 1.0870 0.01794 0.01233 -0.0906 0.4948 1.0000
7.000 1.0775 0.01939 0.01259 -0.0835 0.3261 1.0000
7.250 1.0627 0.02189 0.01412 -0.0770 0.2110 1.0000
7.500 1.0549 0.02411 0.01578 -0.0717 0.1544 1.0000
7.750 1.0535 0.02620 0.01754 -0.0675 0.1217 1.0000
8.000 1.0589 0.02817 0.01934 -0.0644 0.0970 1.0000
8.250 1.0701 0.03016 0.02126 -0.0621 0.0777 1.0000
8.500 1.0895 0.03247 0.02350 -0.0608 0.0626 1.0000
8.750 1.1145 0.03497 0.02601 -0.0604 0.0505 1.0000
9.000 1.1507 0.03841 0.02957 -0.0616 0.0419 1.0000
9.250 1.1756 0.04114 0.03249 -0.0613 0.0369 1.0000
9.500 1.2094 0.04668 0.03830 -0.0626 0.0348 1.0000
9.750 1.2247 0.05203 0.04413 -0.0613 0.0344 1.0000
10.000 1.2283 0.05635 0.04886 -0.0586 0.0341 1.0000
10.250 1.2237 0.05884 0.05179 -0.0548 0.0337 1.0000
10.500 1.2170 0.06212 0.05543 -0.0512 0.0336 1.0000
10.750 1.2047 0.06491 0.05854 -0.0472 0.0333 1.0000
11.000 1.1917 0.06851 0.06243 -0.0440 0.0334 1.0000
11.250 1.1765 0.07228 0.06646 -0.0414 0.0334 1.0000
11.500 1.1596 0.07634 0.07075 -0.0395 0.0335 1.0000
11.750 1.1438 0.08136 0.07597 -0.0385 0.0339 1.0000
12.000 0.9923 0.08556 0.08125 -0.0328 0.0397 1.0000
12.250 0.9605 0.09225 0.08815 -0.0348 0.0407 1.0000
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Polar data table (+)
Polar graphs
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