EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 200,000 Max Cl/Cd: 62.83 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e908-il-200000-n5.txt Download as CSV file: xf-e908-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 908 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4323 0.10602 0.10252 -0.0399 0.9937 0.0069
-9.000 -0.4317 0.10176 0.09829 -0.0416 0.9921 0.0065
-8.750 -0.4292 0.09780 0.09435 -0.0436 0.9903 0.0063
-8.500 -0.4265 0.09350 0.09007 -0.0462 0.9881 0.0061
-8.250 -0.4241 0.08925 0.08584 -0.0490 0.9859 0.0059
-8.000 -0.4209 0.08503 0.08156 -0.0522 0.9839 0.0057
-7.750 -0.4206 0.08042 0.07699 -0.0558 0.9812 0.0056
-7.500 -0.4285 0.07665 0.07335 -0.0574 0.9764 0.0055
-7.250 -0.4251 0.07062 0.06731 -0.0650 0.9722 0.0053
-7.000 -0.4185 0.06444 0.06105 -0.0712 0.9684 0.0052
-6.750 -0.4172 0.05917 0.05568 -0.0738 0.9634 0.0051
-6.500 -0.4056 0.05311 0.04941 -0.0778 0.9601 0.0049
-6.250 -0.3882 0.04694 0.04286 -0.0815 0.9579 0.0046
-6.000 -0.3817 0.04250 0.03814 -0.0806 0.9531 0.0045
-5.750 -0.3646 0.03754 0.03275 -0.0813 0.9499 0.0044
-5.500 -0.3417 0.03303 0.02771 -0.0822 0.9479 0.0042
-5.250 -0.3150 0.02919 0.02330 -0.0830 0.9464 0.0043
-5.000 -0.2858 0.02616 0.01972 -0.0837 0.9454 0.0044
-4.750 -0.2667 0.02417 0.01733 -0.0821 0.9421 0.0047
-4.500 -0.2422 0.02239 0.01518 -0.0814 0.9396 0.0051
-4.250 -0.2138 0.02232 0.01494 -0.0816 0.9373 0.0078
-4.000 -0.1865 0.01985 0.01221 -0.0819 0.9361 0.0106
-3.750 -0.1566 0.01858 0.01079 -0.0824 0.9348 0.0112
-3.500 -0.1253 0.01756 0.00963 -0.0832 0.9336 0.0122
-3.250 -0.0926 0.01677 0.00861 -0.0842 0.9325 0.0149
-3.000 -0.0736 0.01617 0.00780 -0.0825 0.9278 0.0287
-2.750 -0.0466 0.01512 0.00735 -0.0831 0.9253 0.1682
-2.500 -0.0182 0.01417 0.00713 -0.0842 0.9234 0.3519
-2.250 0.0079 0.01334 0.00725 -0.0842 0.9217 0.6088
-2.000 0.0399 0.01326 0.00713 -0.0850 0.9202 0.6597
-1.750 0.0609 0.01328 0.00711 -0.0837 0.9155 0.6863
-1.500 0.0877 0.01325 0.00704 -0.0835 0.9121 0.7106
-1.250 0.1182 0.01320 0.00686 -0.0841 0.9098 0.7298
-1.000 0.1500 0.01312 0.00677 -0.0849 0.9081 0.7472
-0.750 0.1827 0.01304 0.00668 -0.0860 0.9067 0.7652
-0.500 0.1986 0.01312 0.00678 -0.0836 0.8999 0.7833
-0.250 0.2258 0.01301 0.00676 -0.0833 0.8972 0.8123
0.000 0.2544 0.01287 0.00671 -0.0832 0.8952 0.8430
0.250 0.2845 0.01274 0.00664 -0.0835 0.8934 0.8639
0.500 0.3007 0.01279 0.00675 -0.0812 0.8861 0.8821
0.750 0.3323 0.01268 0.00668 -0.0820 0.8837 0.8995
1.000 0.3678 0.01256 0.00662 -0.0837 0.8821 0.9196
1.250 0.4084 0.01244 0.00658 -0.0866 0.8811 0.9456
1.750 0.4666 0.01246 0.00677 -0.0878 0.8707 1.0000
2.000 0.5016 0.01234 0.00672 -0.0894 0.8688 1.0000
2.250 0.5213 0.01247 0.00691 -0.0880 0.8607 1.0000
2.500 0.5538 0.01236 0.00691 -0.0891 0.8576 1.0000
2.750 0.5894 0.01221 0.00690 -0.0907 0.8554 1.0000
3.000 0.6622 0.01054 0.00392 -0.0955 0.5171 1.0000
3.250 0.6361 0.01342 0.00482 -0.0858 0.1386 1.0000
3.500 0.6440 0.01498 0.00571 -0.0822 0.0073 1.0000
3.750 0.6649 0.01552 0.00640 -0.0808 0.0055 1.0000
4.000 0.6841 0.01625 0.00730 -0.0791 0.0048 1.0000
4.250 0.7023 0.01710 0.00828 -0.0772 0.0045 1.0000
4.500 0.7198 0.01817 0.00946 -0.0751 0.0043 1.0000
4.750 0.7398 0.01945 0.01083 -0.0736 0.0042 1.0000
5.000 0.7672 0.02110 0.01259 -0.0734 0.0042 1.0000
5.250 0.8018 0.02324 0.01490 -0.0743 0.0043 1.0000
5.500 0.8392 0.02587 0.01781 -0.0754 0.0045 1.0000
5.750 0.8721 0.02878 0.02110 -0.0755 0.0048 1.0000
6.000 0.8987 0.03193 0.02476 -0.0743 0.0052 1.0000
6.250 0.9194 0.03511 0.02833 -0.0724 0.0056 1.0000
6.500 0.9353 0.03839 0.03199 -0.0698 0.0061 1.0000
6.750 0.9468 0.04185 0.03580 -0.0667 0.0065 1.0000
7.000 0.9533 0.04558 0.03988 -0.0633 0.0070 1.0000
12.500 0.6877 0.14443 0.14160 -0.0557 0.0176 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 908 AIRFOIL (e908-il)