EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 100,000 Max Cl/Cd: 49.03 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e851-il-100000.txt Download as CSV file: xf-e851-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E851 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4785 0.09749 0.09277 -0.0410 1.0000 0.0800
-8.500 -0.4985 0.09461 0.09001 -0.0433 1.0000 0.0804
-8.250 -0.5218 0.09171 0.08724 -0.0446 1.0000 0.0805
-8.000 -0.4860 0.08764 0.08312 -0.0377 1.0000 0.0848
-7.750 -0.4953 0.08509 0.08066 -0.0364 1.0000 0.0870
-7.500 -0.5125 0.08267 0.07835 -0.0351 1.0000 0.0885
-7.250 -0.5291 0.07914 0.07490 -0.0367 1.0000 0.0902
-7.000 -0.5585 0.07482 0.07045 -0.0426 1.0000 0.0930
-6.750 -0.5644 0.07038 0.06602 -0.0424 1.0000 0.0952
-6.500 -0.5568 0.06767 0.06340 -0.0394 1.0000 0.0981
-6.000 -0.5577 0.06007 0.05560 -0.0409 1.0000 0.1107
-5.750 -0.5538 0.05630 0.05158 -0.0425 1.0000 0.1221
-5.500 -0.5424 0.05303 0.04831 -0.0415 1.0000 0.1282
-5.250 -0.5310 0.04954 0.04465 -0.0420 1.0000 0.1420
-5.000 -0.4812 0.03622 0.02939 -0.0453 1.0000 0.0351
-4.750 -0.4531 0.03353 0.02578 -0.0443 1.0000 0.0301
-4.500 -0.4286 0.03079 0.02260 -0.0440 1.0000 0.0296
-4.250 -0.4048 0.02740 0.01899 -0.0446 1.0000 0.0343
-4.000 -0.3796 0.02596 0.01705 -0.0439 1.0000 0.0400
-3.750 -0.3531 0.02405 0.01481 -0.0429 1.0000 0.0422
-3.500 -0.3281 0.02173 0.01255 -0.0423 1.0000 0.0477
-3.250 -0.3027 0.02004 0.01098 -0.0418 1.0000 0.0755
-3.000 -0.2723 0.01606 0.00928 -0.0433 1.0000 0.4902
-2.750 -0.2564 0.01636 0.00975 -0.0399 1.0000 0.6148
-2.500 -0.2408 0.01663 0.01002 -0.0367 1.0000 0.6677
-2.250 -0.2251 0.01681 0.01016 -0.0338 1.0000 0.7060
-2.000 -0.2098 0.01691 0.01023 -0.0308 1.0000 0.7390
-1.750 -0.1965 0.01698 0.01029 -0.0273 1.0000 0.7724
-1.500 -0.1831 0.01696 0.01026 -0.0241 1.0000 0.8020
-1.250 -0.1656 0.01690 0.01003 -0.0222 1.0000 0.8249
-1.000 -0.1464 0.01684 0.00990 -0.0208 1.0000 0.8459
-0.750 -0.1278 0.01676 0.00978 -0.0194 1.0000 0.8700
-0.500 -0.1084 0.01666 0.00968 -0.0181 1.0000 0.9019
-0.250 -0.0737 0.01645 0.00948 -0.0205 1.0000 0.9628
0.000 -0.0417 0.01647 0.00934 -0.0235 1.0000 1.0000
0.250 -0.0098 0.01676 0.00941 -0.0261 1.0000 1.0000
0.500 0.0187 0.01711 0.00960 -0.0277 1.0000 1.0000
0.750 0.0450 0.01748 0.00985 -0.0287 1.0000 1.0000
1.000 0.0697 0.01789 0.01016 -0.0293 1.0000 1.0000
1.250 0.0933 0.01832 0.01052 -0.0297 1.0000 1.0000
1.500 0.1282 0.01902 0.01118 -0.0323 0.9954 1.0000
1.750 0.1689 0.01978 0.01192 -0.0359 0.9870 1.0000
2.000 0.2111 0.02062 0.01276 -0.0397 0.9791 1.0000
2.250 0.2513 0.02129 0.01346 -0.0430 0.9701 1.0000
2.500 0.2886 0.02182 0.01404 -0.0457 0.9598 1.0000
2.750 0.3275 0.02236 0.01475 -0.0486 0.9492 1.0000
3.000 0.3686 0.02284 0.01536 -0.0518 0.9379 1.0000
3.250 0.4113 0.02324 0.01590 -0.0550 0.9258 1.0000
3.500 0.4554 0.02347 0.01632 -0.0582 0.9120 1.0000
3.750 0.5060 0.02338 0.01649 -0.0620 0.8955 1.0000
4.000 0.5750 0.02221 0.01580 -0.0674 0.8708 1.0000
4.250 0.6796 0.01851 0.01278 -0.0758 0.8374 1.0000
4.500 0.7379 0.01505 0.00974 -0.0749 0.7585 1.0000
4.750 0.7450 0.01758 0.00888 -0.0676 0.1726 1.0000
5.000 0.7524 0.02028 0.01087 -0.0638 0.0985 1.0000
5.250 0.7694 0.02244 0.01282 -0.0615 0.0644 1.0000
5.500 0.7934 0.02479 0.01511 -0.0605 0.0429 1.0000
5.750 0.8295 0.02900 0.01927 -0.0613 0.0363 1.0000
6.000 0.8602 0.03196 0.02284 -0.0604 0.0349 1.0000
6.250 0.8843 0.03444 0.02582 -0.0588 0.0319 1.0000
6.500 0.9024 0.03664 0.02811 -0.0579 0.0263 1.0000
6.750 0.9181 0.04142 0.03332 -0.0561 0.0253 1.0000
7.000 0.9364 0.04376 0.03613 -0.0537 0.0262 1.0000
7.250 0.9460 0.04873 0.04203 -0.0492 0.0310 1.0000
7.500 0.9527 0.05347 0.04712 -0.0465 0.0340 1.0000
9.500 0.8657 0.09476 0.09067 -0.0265 0.0870 1.0000
9.750 0.8388 0.09881 0.09481 -0.0259 0.0870 1.0000
10.000 0.8129 0.10362 0.09971 -0.0271 0.0869 1.0000
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Polar data table (+)
Polar graphs
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