EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E850 AIRFOIL (e850-il) Reynolds number: 200,000 Max Cl/Cd: 64.78 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e850-il-200000.txt Download as CSV file: xf-e850-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5186 0.08797 0.08457 -0.0367 1.0000 0.0341
-8.250 -0.5295 0.08381 0.08047 -0.0387 1.0000 0.0341
-8.000 -0.5454 0.08042 0.07712 -0.0392 1.0000 0.0341
-7.750 -0.5596 0.07695 0.07363 -0.0401 1.0000 0.0341
-7.500 -0.5701 0.07378 0.07038 -0.0404 1.0000 0.0342
-7.250 -0.5779 0.07073 0.06720 -0.0403 1.0000 0.0344
-7.000 -0.5819 0.06772 0.06402 -0.0399 1.0000 0.0345
-6.750 -0.5823 0.06459 0.06069 -0.0394 1.0000 0.0346
-6.500 -0.5879 0.05631 0.05245 -0.0400 1.0000 0.0359
-6.250 -0.5813 0.05269 0.04883 -0.0393 1.0000 0.0371
-6.000 -0.5725 0.04950 0.04556 -0.0388 1.0000 0.0387
-5.750 -0.5611 0.04617 0.04203 -0.0387 1.0000 0.0411
-5.500 -0.5400 0.04663 0.04166 -0.0378 1.0000 0.0471
-4.250 -0.4268 0.02445 0.01762 -0.0360 1.0000 0.0197
-4.000 -0.3996 0.02159 0.01435 -0.0355 1.0000 0.0171
-3.750 -0.3724 0.01934 0.01176 -0.0346 1.0000 0.0152
-3.500 -0.3464 0.01764 0.00987 -0.0337 1.0000 0.0140
-3.250 -0.3207 0.01633 0.00844 -0.0331 1.0000 0.0136
-3.000 -0.2948 0.01530 0.00728 -0.0328 1.0000 0.0139
-2.750 -0.2686 0.01456 0.00634 -0.0326 1.0000 0.0154
-2.500 -0.2426 0.01407 0.00563 -0.0322 1.0000 0.0201
-2.250 -0.2143 0.01173 0.00527 -0.0338 1.0000 0.4865
-2.000 -0.1964 0.01173 0.00586 -0.0314 1.0000 0.6476
-1.750 -0.1764 0.01186 0.00595 -0.0296 1.0000 0.6881
-1.500 -0.1557 0.01195 0.00607 -0.0281 1.0000 0.7159
-1.250 -0.1334 0.01199 0.00610 -0.0272 1.0000 0.7323
-1.000 -0.1109 0.01204 0.00614 -0.0264 1.0000 0.7460
-0.750 -0.0887 0.01209 0.00620 -0.0256 1.0000 0.7604
-0.500 -0.0668 0.01215 0.00629 -0.0248 1.0000 0.7760
-0.250 -0.0417 0.01226 0.00640 -0.0246 0.9989 0.7940
0.000 -0.0069 0.01252 0.00673 -0.0264 0.9945 0.8144
0.250 0.0253 0.01265 0.00694 -0.0276 0.9894 0.8398
0.750 0.1081 0.01284 0.00744 -0.0338 0.9812 0.9795
1.000 0.1437 0.01292 0.00748 -0.0362 0.9743 1.0000
1.250 0.1870 0.01324 0.00777 -0.0400 0.9696 1.0000
1.500 0.2227 0.01336 0.00790 -0.0421 0.9622 1.0000
1.750 0.2683 0.01356 0.00815 -0.0460 0.9567 1.0000
2.000 0.3061 0.01356 0.00822 -0.0483 0.9476 1.0000
2.250 0.3526 0.01348 0.00825 -0.0520 0.9389 1.0000
2.500 0.4104 0.01291 0.00799 -0.0572 0.9249 1.0000
2.750 0.4809 0.01165 0.00700 -0.0641 0.9071 1.0000
3.000 0.5500 0.00979 0.00544 -0.0697 0.8729 1.0000
3.250 0.6070 0.00937 0.00414 -0.0723 0.5738 1.0000
3.500 0.5943 0.01241 0.00497 -0.0650 0.1533 1.0000
3.750 0.6061 0.01461 0.00647 -0.0620 0.0404 1.0000
4.000 0.6246 0.01628 0.00814 -0.0599 0.0250 1.0000
4.250 0.6482 0.01788 0.00983 -0.0585 0.0227 1.0000
4.500 0.6762 0.01997 0.01204 -0.0578 0.0219 1.0000
4.750 0.7065 0.02259 0.01493 -0.0572 0.0224 1.0000
5.000 0.7341 0.02515 0.01785 -0.0561 0.0215 1.0000
5.500 0.7735 0.03029 0.02364 -0.0533 0.0139 1.0000
5.750 0.7759 0.02615 0.02081 -0.0450 0.0333 1.0000
6.000 0.7876 0.03051 0.02556 -0.0424 0.0349 1.0000
6.250 0.7987 0.03441 0.02982 -0.0398 0.0331 1.0000
6.500 0.8071 0.03853 0.03423 -0.0374 0.0316 1.0000
6.750 0.8134 0.04279 0.03873 -0.0353 0.0304 1.0000
7.000 0.8175 0.04716 0.04328 -0.0333 0.0294 1.0000
7.250 0.8197 0.05162 0.04789 -0.0314 0.0286 1.0000
7.500 0.8203 0.05641 0.05277 -0.0299 0.0279 1.0000
7.750 0.8159 0.06249 0.05892 -0.0286 0.0273 1.0000
8.750 0.7514 0.08286 0.07973 -0.0218 0.0266 1.0000
9.000 0.7337 0.08739 0.08434 -0.0222 0.0266 1.0000
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Polar data table (+)
Polar graphs
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