EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 500,000 Max Cl/Cd: 110.76 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e851-il-500000.txt Download as CSV file: xf-e851-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4789 0.08530 0.08318 -0.0354 1.0000 0.0116
-8.250 -0.4912 0.08243 0.08036 -0.0343 1.0000 0.0117
-8.000 -0.5019 0.07906 0.07704 -0.0346 0.9994 0.0116
-7.750 -0.4936 0.07197 0.06996 -0.0443 0.9954 0.0118
-7.500 -0.4810 0.06102 0.05889 -0.0624 0.9880 0.0117
-7.250 -0.4646 0.05391 0.05157 -0.0716 0.9835 0.0121
-7.000 -0.4440 0.04772 0.04512 -0.0782 0.9805 0.0128
-6.750 -0.4291 0.04312 0.04028 -0.0804 0.9741 0.0137
-6.500 -0.4034 0.03874 0.03559 -0.0834 0.9713 0.0151
-6.250 -0.3669 0.03800 0.03457 -0.0848 0.9699 0.0173
-6.000 -0.3450 0.03464 0.03088 -0.0858 0.9656 0.0174
-5.750 -0.3219 0.03131 0.02722 -0.0866 0.9615 0.0174
-5.250 -0.2676 0.01856 0.01333 -0.0883 0.9578 0.0070
-5.000 -0.2359 0.01567 0.01003 -0.0891 0.9568 0.0062
-4.750 -0.2032 0.01371 0.00785 -0.0901 0.9560 0.0058
-4.500 -0.1831 0.01257 0.00655 -0.0885 0.9503 0.0057
-4.250 -0.1518 0.01151 0.00532 -0.0894 0.9483 0.0059
-4.000 -0.1181 0.01077 0.00439 -0.0907 0.9469 0.0070
-3.750 -0.0840 0.00987 0.00362 -0.0922 0.9458 0.0630
-3.500 -0.0526 0.00844 0.00314 -0.0944 0.9448 0.3001
-3.250 -0.0203 0.00776 0.00306 -0.0960 0.9438 0.4790
-3.000 0.0078 0.00768 0.00300 -0.0962 0.9406 0.5092
-2.750 0.0362 0.00762 0.00291 -0.0964 0.9372 0.5388
-2.500 0.0680 0.00755 0.00282 -0.0973 0.9351 0.5558
-2.250 0.1006 0.00746 0.00272 -0.0984 0.9333 0.5713
-2.000 0.1337 0.00738 0.00266 -0.0996 0.9318 0.5895
-1.750 0.1671 0.00731 0.00260 -0.1008 0.9304 0.6054
-1.500 0.1919 0.00731 0.00260 -0.1003 0.9258 0.6164
-1.250 0.2214 0.00726 0.00255 -0.1007 0.9227 0.6260
-1.000 0.2529 0.00720 0.00249 -0.1016 0.9203 0.6356
-0.750 0.2853 0.00711 0.00243 -0.1026 0.9182 0.6446
-0.500 0.3128 0.00710 0.00244 -0.1026 0.9142 0.6540
-0.250 0.3405 0.00707 0.00245 -0.1026 0.9098 0.6643
0.000 0.3716 0.00699 0.00241 -0.1033 0.9063 0.6750
0.250 0.4006 0.00694 0.00241 -0.1036 0.9019 0.6860
0.500 0.4275 0.00689 0.00241 -0.1034 0.8958 0.6978
0.750 0.4588 0.00679 0.00237 -0.1040 0.8908 0.7107
1.000 0.4838 0.00673 0.00238 -0.1032 0.8822 0.7246
1.250 0.5113 0.00666 0.00241 -0.1030 0.8741 0.7398
1.500 0.5389 0.00656 0.00236 -0.1027 0.8638 0.7566
1.750 0.5639 0.00645 0.00233 -0.1017 0.8499 0.7748
2.250 0.6139 0.00630 0.00237 -0.1000 0.8247 0.8191
2.500 0.6369 0.00623 0.00247 -0.0987 0.8090 0.8469
2.750 0.6568 0.00614 0.00246 -0.0965 0.7794 0.8815
3.000 0.6745 0.00609 0.00242 -0.0938 0.7347 0.9341
3.250 0.6992 0.00647 0.00245 -0.0929 0.6337 1.0000
3.500 0.7000 0.00795 0.00291 -0.0877 0.4276 1.0000
3.750 0.7051 0.00970 0.00354 -0.0839 0.1996 1.0000
4.000 0.7200 0.01089 0.00406 -0.0820 0.0737 1.0000
4.250 0.7407 0.01160 0.00449 -0.0809 0.0255 1.0000
4.500 0.7607 0.01257 0.00548 -0.0791 0.0051 1.0000
4.750 0.7822 0.01335 0.00640 -0.0777 0.0045 1.0000
5.000 0.8021 0.01438 0.00756 -0.0759 0.0042 1.0000
5.250 0.8212 0.01569 0.00902 -0.0740 0.0041 1.0000
5.500 0.8420 0.01741 0.01098 -0.0724 0.0042 1.0000
5.750 0.8665 0.01987 0.01369 -0.0712 0.0045 1.0000
6.000 0.8916 0.02324 0.01740 -0.0701 0.0049 1.0000
6.250 0.9153 0.02585 0.02021 -0.0689 0.0062 1.0000
6.500 0.9177 0.03900 0.03440 -0.0627 0.0136 1.0000
6.750 0.9281 0.04245 0.03815 -0.0600 0.0135 1.0000
7.000 0.9362 0.04598 0.04197 -0.0571 0.0135 1.0000
7.250 0.9422 0.04947 0.04574 -0.0541 0.0135 1.0000
7.500 0.9461 0.05292 0.04945 -0.0512 0.0134 1.0000
7.750 0.9481 0.05627 0.05305 -0.0481 0.0133 1.0000
8.000 0.9625 0.05739 0.05437 -0.0457 0.0125 1.0000
8.250 0.9707 0.06019 0.05737 -0.0432 0.0114 1.0000
8.500 0.9666 0.06400 0.06137 -0.0403 0.0110 1.0000
8.750 0.9565 0.06764 0.06517 -0.0372 0.0107 1.0000
9.000 0.9398 0.07098 0.06863 -0.0337 0.0106 1.0000
9.250 0.9218 0.07463 0.07239 -0.0314 0.0106 1.0000
9.500 0.9018 0.07895 0.07682 -0.0306 0.0107 1.0000
9.750 0.8818 0.08405 0.08200 -0.0317 0.0109 1.0000
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Polar data table (+)
Polar graphs
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