EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 200,000 Max Cl/Cd: 47.82 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e908-il-200000.txt Download as CSV file: xf-e908-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5143 0.09375 0.09068 -0.0259 1.0000 0.0291
-7.500 -0.5250 0.09104 0.08802 -0.0249 1.0000 0.0296
-7.250 -0.5397 0.08858 0.08561 -0.0237 1.0000 0.0296
-7.000 -0.5509 0.08543 0.08251 -0.0240 1.0000 0.0298
-6.750 -0.5571 0.08121 0.07831 -0.0265 1.0000 0.0300
-6.500 -0.5603 0.07670 0.07379 -0.0290 1.0000 0.0308
-6.250 -0.5601 0.07215 0.06919 -0.0313 1.0000 0.0317
-6.000 -0.5566 0.06743 0.06438 -0.0336 1.0000 0.0327
-5.750 -0.5485 0.06220 0.05898 -0.0363 1.0000 0.0348
-5.500 -0.5284 0.05836 0.05452 -0.0396 1.0000 0.0376
-5.250 -0.5233 0.05054 0.04668 -0.0414 1.0000 0.0394
-5.000 -0.5103 0.04772 0.04385 -0.0412 1.0000 0.0419
-4.750 -0.4867 0.04373 0.03906 -0.0432 1.0000 0.0512
-4.500 -0.4722 0.04095 0.03635 -0.0436 1.0000 0.0656
-4.250 -0.4355 0.03820 0.03346 -0.0475 0.9959 0.0805
-3.750 -0.3478 0.02741 0.02081 -0.0504 0.9904 0.0359
-3.500 -0.3099 0.02443 0.01714 -0.0510 0.9878 0.0266
-3.250 -0.2735 0.02298 0.01546 -0.0524 0.9851 0.0244
-3.000 -0.2364 0.02134 0.01361 -0.0539 0.9832 0.0233
-2.750 -0.2057 0.02011 0.01229 -0.0544 0.9788 0.0230
-2.500 -0.1723 0.01927 0.01132 -0.0556 0.9751 0.0238
-2.250 -0.1352 0.01853 0.01036 -0.0574 0.9724 0.0368
-2.000 -0.1088 0.01604 0.01062 -0.0582 0.9712 0.6692
-1.750 -0.0897 0.01599 0.01083 -0.0558 0.9651 0.7749
-1.500 -0.0621 0.01612 0.01094 -0.0554 0.9608 0.8172
-1.250 -0.0311 0.01632 0.01107 -0.0559 0.9571 0.8451
-1.000 -0.0090 0.01623 0.01095 -0.0548 0.9506 0.8703
-0.750 0.0236 0.01634 0.01102 -0.0557 0.9471 0.8982
-0.500 0.0587 0.01638 0.01099 -0.0574 0.9429 0.9357
-0.250 0.1013 0.01638 0.01091 -0.0612 0.9382 1.0000
0.000 0.1398 0.01658 0.01101 -0.0640 0.9349 1.0000
0.250 0.1808 0.01685 0.01119 -0.0673 0.9327 1.0000
0.500 0.2041 0.01687 0.01116 -0.0670 0.9246 1.0000
0.750 0.2426 0.01704 0.01129 -0.0697 0.9215 1.0000
1.000 0.2707 0.01718 0.01139 -0.0702 0.9152 1.0000
1.250 0.3046 0.01730 0.01150 -0.0719 0.9105 1.0000
1.500 0.3438 0.01742 0.01163 -0.0745 0.9079 1.0000
1.750 0.3679 0.01754 0.01177 -0.0742 0.9000 1.0000
2.000 0.4046 0.01762 0.01194 -0.0763 0.8964 1.0000
2.250 0.4411 0.01768 0.01208 -0.0783 0.8928 1.0000
2.500 0.4672 0.01775 0.01221 -0.0783 0.8849 1.0000
2.750 0.5075 0.01770 0.01227 -0.0808 0.8821 1.0000
3.000 0.5322 0.01776 0.01244 -0.0804 0.8733 1.0000
3.250 0.5728 0.01758 0.01253 -0.0828 0.8699 1.0000
3.500 0.6595 0.01379 0.00525 -0.0847 0.1108 1.0000
3.750 0.6693 0.01531 0.00640 -0.0811 0.0273 1.0000
4.000 0.6868 0.01618 0.00744 -0.0789 0.0248 1.0000
4.250 0.7030 0.01724 0.00860 -0.0764 0.0236 1.0000
4.500 0.7220 0.01847 0.00988 -0.0746 0.0213 1.0000
4.750 0.7502 0.02090 0.01227 -0.0750 0.0157 1.0000
5.000 0.7928 0.02369 0.01516 -0.0772 0.0157 1.0000
5.250 0.8261 0.02511 0.01687 -0.0773 0.0170 1.0000
5.750 0.9290 0.03532 0.02854 -0.0768 0.0686 1.0000
6.000 0.9420 0.03782 0.03129 -0.0744 0.0578 1.0000
6.250 0.9600 0.04090 0.03442 -0.0731 0.0530 1.0000
6.500 0.9666 0.04320 0.03723 -0.0690 0.0457 1.0000
6.750 0.9791 0.04590 0.04012 -0.0667 0.0420 1.0000
7.000 0.9936 0.05076 0.04490 -0.0661 0.0396 1.0000
7.250 0.9888 0.05701 0.05152 -0.0622 0.0381 1.0000
7.500 0.9942 0.05551 0.05064 -0.0564 0.0337 1.0000
7.750 0.9969 0.05858 0.05396 -0.0531 0.0316 1.0000
8.000 0.9978 0.06173 0.05729 -0.0501 0.0302 1.0000
8.250 0.9978 0.06501 0.06070 -0.0474 0.0290 1.0000
8.500 0.9971 0.06879 0.06454 -0.0452 0.0281 1.0000
10.500 0.7424 0.10516 0.10238 -0.0362 0.0328 1.0000
10.750 0.7308 0.11216 0.10936 -0.0403 0.0329 1.0000
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Polar data table (+)
Polar graphs
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