EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER E850 AIRFOIL (e850-il) Reynolds number: 100,000 Max Cl/Cd: 38.31 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e850-il-100000.txt Download as CSV file: xf-e850-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5345 0.09099 0.08633 -0.0342 1.0000 0.0849
-8.000 -0.5570 0.08767 0.08312 -0.0366 1.0000 0.0853
-7.750 -0.5786 0.08375 0.07919 -0.0409 1.0000 0.0857
-7.500 -0.5555 0.08074 0.07631 -0.0327 1.0000 0.0900
-7.250 -0.5614 0.07696 0.07257 -0.0339 1.0000 0.0930
-7.000 -0.5747 0.07268 0.06823 -0.0372 1.0000 0.0967
-6.750 -0.5882 0.06808 0.06347 -0.0401 1.0000 0.1004
-6.500 -0.5777 0.06507 0.06058 -0.0371 1.0000 0.1051
-6.250 -0.5820 0.06076 0.05603 -0.0395 1.0000 0.1141
-6.000 -0.5725 0.05763 0.05292 -0.0381 1.0000 0.1205
-5.750 -0.5658 0.05394 0.04914 -0.0382 1.0000 0.1318
-5.500 -0.5561 0.05049 0.04541 -0.0384 1.0000 0.1467
-5.000 -0.4938 0.03583 0.02865 -0.0406 1.0000 0.0424
-4.750 -0.4669 0.03257 0.02463 -0.0394 1.0000 0.0334
-4.500 -0.4432 0.02908 0.02077 -0.0390 1.0000 0.0310
-4.250 -0.4175 0.02639 0.01766 -0.0383 1.0000 0.0289
-4.000 -0.3908 0.02407 0.01495 -0.0374 1.0000 0.0275
-3.750 -0.3648 0.02213 0.01278 -0.0364 1.0000 0.0273
-3.500 -0.3399 0.02053 0.01107 -0.0354 1.0000 0.0281
-3.250 -0.3152 0.01919 0.00963 -0.0346 1.0000 0.0306
-3.000 -0.2899 0.01806 0.00840 -0.0342 1.0000 0.0423
-2.750 -0.2679 0.01453 0.00762 -0.0334 1.0000 0.6059
-2.500 -0.2651 0.01506 0.00852 -0.0256 1.0000 0.7233
-2.250 -0.2499 0.01508 0.00844 -0.0221 1.0000 0.7588
-2.000 -0.2373 0.01504 0.00837 -0.0180 1.0000 0.7913
-1.750 -0.2225 0.01490 0.00803 -0.0149 1.0000 0.8186
-1.500 -0.2034 0.01472 0.00775 -0.0132 1.0000 0.8389
-1.250 -0.1837 0.01455 0.00748 -0.0117 1.0000 0.8598
-1.000 -0.1644 0.01436 0.00725 -0.0101 1.0000 0.8838
-0.750 -0.1426 0.01417 0.00704 -0.0091 1.0000 0.9154
-0.500 -0.1004 0.01399 0.00683 -0.0127 1.0000 0.9656
-0.250 -0.0658 0.01386 0.00656 -0.0160 1.0000 1.0000
0.000 -0.0338 0.01396 0.00645 -0.0185 1.0000 1.0000
0.250 -0.0044 0.01413 0.00648 -0.0201 1.0000 1.0000
0.500 0.0230 0.01434 0.00659 -0.0211 1.0000 1.0000
0.750 0.0489 0.01458 0.00675 -0.0216 1.0000 1.0000
1.000 0.0737 0.01485 0.00696 -0.0219 1.0000 1.0000
1.250 0.0977 0.01514 0.00723 -0.0220 1.0000 1.0000
1.500 0.1212 0.01546 0.00754 -0.0220 1.0000 1.0000
1.750 0.1441 0.01581 0.00789 -0.0220 1.0000 1.0000
2.000 0.1665 0.01619 0.00829 -0.0218 1.0000 1.0000
2.250 0.1885 0.01660 0.00875 -0.0217 1.0000 1.0000
2.500 0.2100 0.01705 0.00927 -0.0215 1.0000 1.0000
2.750 0.2310 0.01754 0.00985 -0.0213 1.0000 1.0000
3.000 0.2660 0.01832 0.01078 -0.0239 0.9944 1.0000
3.250 0.3245 0.01922 0.01213 -0.0308 0.9771 1.0000
3.500 0.3976 0.01956 0.01290 -0.0395 0.9506 1.0000
3.750 0.5639 0.01472 0.00934 -0.0571 0.8505 1.0000
4.000 0.6097 0.01865 0.00916 -0.0555 0.0768 1.0000
4.250 0.6314 0.02077 0.01125 -0.0535 0.0585 1.0000
4.500 0.6578 0.02271 0.01316 -0.0529 0.0432 1.0000
4.750 0.6897 0.02579 0.01625 -0.0530 0.0393 1.0000
5.000 0.7211 0.02903 0.01979 -0.0527 0.0391 1.0000
5.250 0.7494 0.03145 0.02276 -0.0510 0.0412 1.0000
5.500 0.7738 0.03551 0.02754 -0.0486 0.0469 1.0000
5.750 0.7971 0.04046 0.03314 -0.0458 0.0612 1.0000
7.250 0.8692 0.06973 0.06482 -0.0330 0.1147 1.0000
8.250 0.8799 0.08740 0.08262 -0.0290 0.0766 1.0000
8.500 0.8623 0.08999 0.08548 -0.0275 0.0763 1.0000
8.750 0.8437 0.09314 0.08877 -0.0266 0.0760 1.0000
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Polar data table (+)
Polar graphs
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