EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 339 AIRFOIL (e339-il) Reynolds number: 200,000 Max Cl/Cd: 68.25 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e339-il-200000-n5.txt Download as CSV file: xf-e339-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 339 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2771 0.10181 0.09845 -0.0320 1.0000 0.0212
-9.250 -0.2766 0.09851 0.09520 -0.0331 1.0000 0.0216
-9.000 -0.2791 0.09484 0.09159 -0.0348 1.0000 0.0221
-8.750 -0.2723 0.08938 0.08616 -0.0410 0.9712 0.0223
-8.500 -0.2413 0.08037 0.07703 -0.0582 0.8952 0.0224
-8.250 -0.2058 0.07494 0.07137 -0.0668 0.8399 0.0228
-8.000 -0.2012 0.07069 0.06691 -0.0711 0.7980 0.0229
-7.750 -0.2079 0.06736 0.06342 -0.0718 0.7686 0.0229
-7.500 -0.2105 0.06485 0.06078 -0.0709 0.7456 0.0232
-7.250 -0.2114 0.06199 0.05777 -0.0705 0.7266 0.0235
-7.000 -0.2108 0.05907 0.05471 -0.0698 0.7097 0.0237
-6.750 -0.2085 0.05610 0.05157 -0.0689 0.6955 0.0242
-6.250 -0.2054 0.04683 0.04171 -0.0653 0.6721 0.0155
-6.000 -0.1966 0.04414 0.03881 -0.0637 0.6601 0.0151
-5.750 -0.1866 0.04115 0.03554 -0.0617 0.6493 0.0151
-5.500 -0.1729 0.03930 0.03349 -0.0603 0.6378 0.0172
-5.000 -0.1474 0.03163 0.02489 -0.0547 0.6194 0.0157
-4.750 -0.1302 0.02966 0.02265 -0.0531 0.6093 0.0155
-4.500 -0.1116 0.02763 0.02029 -0.0513 0.5996 0.0152
-4.250 -0.0915 0.02546 0.01775 -0.0496 0.5904 0.0148
-4.000 -0.0696 0.02347 0.01535 -0.0481 0.5816 0.0145
-3.750 -0.0457 0.02178 0.01331 -0.0469 0.5732 0.0144
-3.500 -0.0206 0.02033 0.01152 -0.0459 0.5645 0.0143
-3.250 0.0053 0.01913 0.01006 -0.0451 0.5563 0.0145
-3.000 0.0312 0.01817 0.00889 -0.0443 0.5478 0.0147
-2.750 0.0566 0.01738 0.00795 -0.0436 0.5398 0.0151
-2.500 0.0813 0.01670 0.00713 -0.0428 0.5320 0.0156
-2.250 0.1050 0.01616 0.00651 -0.0418 0.5254 0.0163
-2.000 0.1290 0.01572 0.00604 -0.0410 0.5182 0.0174
-1.750 0.1527 0.01538 0.00558 -0.0401 0.5116 0.0190
-1.500 0.1767 0.01511 0.00530 -0.0393 0.5049 0.0229
-1.250 0.2007 0.01483 0.00497 -0.0385 0.4982 0.0269
-1.000 0.2244 0.01460 0.00467 -0.0376 0.4926 0.0351
-0.750 0.2478 0.01426 0.00445 -0.0367 0.4869 0.0628
-0.500 0.2672 0.01359 0.00427 -0.0353 0.4815 0.2029
0.000 0.3215 0.01322 0.00600 -0.0313 0.4709 0.9303
0.250 0.4248 0.01382 0.00628 -0.0457 0.4620 0.9562
0.500 0.4498 0.01392 0.00622 -0.0452 0.4578 0.9615
0.750 0.4805 0.01391 0.00614 -0.0459 0.4528 0.9631
1.000 0.5107 0.01392 0.00606 -0.0465 0.4477 0.9647
1.250 0.5394 0.01397 0.00598 -0.0469 0.4432 0.9665
1.500 0.5670 0.01403 0.00595 -0.0470 0.4390 0.9685
1.750 0.5930 0.01407 0.00596 -0.0468 0.4346 0.9705
2.000 0.6168 0.01415 0.00598 -0.0461 0.4305 0.9729
2.250 0.6436 0.01422 0.00597 -0.0461 0.4265 0.9744
2.500 0.6724 0.01430 0.00598 -0.0466 0.4228 0.9756
2.750 0.7011 0.01436 0.00603 -0.0470 0.4184 0.9770
3.000 0.7280 0.01444 0.00609 -0.0470 0.4146 0.9784
3.250 0.7542 0.01454 0.00615 -0.0469 0.4109 0.9798
3.500 0.7803 0.01468 0.00621 -0.0468 0.4076 0.9815
3.750 0.8048 0.01478 0.00635 -0.0464 0.4037 0.9831
4.000 0.8288 0.01490 0.00648 -0.0458 0.3999 0.9844
4.250 0.8572 0.01501 0.00659 -0.0463 0.3962 0.9856
4.500 0.8849 0.01515 0.00668 -0.0465 0.3928 0.9867
4.750 0.9111 0.01530 0.00684 -0.0465 0.3895 0.9878
5.000 0.9368 0.01543 0.00705 -0.0464 0.3856 0.9889
5.250 0.9621 0.01558 0.00722 -0.0462 0.3818 0.9901
5.500 0.9880 0.01574 0.00738 -0.0462 0.3783 0.9916
5.750 1.0134 0.01595 0.00755 -0.0460 0.3751 0.9930
6.000 1.0377 0.01612 0.00783 -0.0457 0.3714 0.9941
6.250 1.0634 0.01629 0.00807 -0.0456 0.3672 0.9952
6.500 1.0887 0.01647 0.00829 -0.0455 0.3635 0.9963
6.750 1.1137 0.01668 0.00850 -0.0454 0.3600 0.9975
7.000 1.1387 0.01690 0.00879 -0.0452 0.3561 0.9988
7.250 1.1632 0.01711 0.00911 -0.0450 0.3517 1.0000
7.500 1.1809 0.01732 0.00938 -0.0434 0.3478 1.0000
7.750 1.1984 0.01756 0.00962 -0.0417 0.3443 1.0000
8.000 1.2149 0.01780 0.00996 -0.0399 0.3403 1.0000
8.250 1.2302 0.01803 0.01030 -0.0378 0.3357 1.0000
8.500 1.2449 0.01825 0.01058 -0.0356 0.3313 1.0000
8.750 1.2593 0.01850 0.01082 -0.0334 0.3274 1.0000
9.000 1.2714 0.01874 0.01122 -0.0308 0.3223 1.0000
9.250 1.2824 0.01897 0.01154 -0.0280 0.3173 1.0000
9.500 1.2925 0.01920 0.01178 -0.0250 0.3130 1.0000
9.750 1.3013 0.01946 0.01216 -0.0219 0.3082 1.0000
10.000 1.3091 0.01970 0.01250 -0.0185 0.3030 1.0000
10.250 1.3167 0.01996 0.01278 -0.0152 0.2984 1.0000
10.500 1.3260 0.02028 0.01321 -0.0124 0.2930 1.0000
10.750 1.3342 0.02061 0.01362 -0.0094 0.2870 1.0000
11.000 1.3434 0.02100 0.01406 -0.0068 0.2813 1.0000
11.250 1.3534 0.02147 0.01464 -0.0044 0.2741 1.0000
11.500 1.3616 0.02202 0.01522 -0.0020 0.2672 1.0000
11.750 1.3704 0.02267 0.01597 0.0001 0.2589 1.0000
12.000 1.3773 0.02345 0.01681 0.0022 0.2514 1.0000
12.250 1.3832 0.02436 0.01780 0.0041 0.2430 1.0000
12.500 1.3878 0.02545 0.01896 0.0060 0.2346 1.0000
12.750 1.3893 0.02681 0.02035 0.0077 0.2263 1.0000
13.000 1.3917 0.02830 0.02193 0.0091 0.2173 1.0000
13.250 1.3906 0.03015 0.02382 0.0104 0.2087 1.0000
13.500 1.3879 0.03228 0.02601 0.0114 0.2000 1.0000
13.750 1.3850 0.03461 0.02841 0.0121 0.1911 1.0000
14.000 1.3786 0.03736 0.03119 0.0126 0.1831 1.0000
14.250 1.3720 0.04031 0.03420 0.0129 0.1746 1.0000
14.500 1.3645 0.04346 0.03740 0.0130 0.1668 1.0000
14.750 1.3537 0.04705 0.04103 0.0128 0.1593 1.0000
15.000 1.3460 0.05046 0.04451 0.0125 0.1520 1.0000
15.500 1.3264 0.05811 0.05228 0.0114 0.1386 1.0000
15.750 1.3153 0.06228 0.05648 0.0105 0.1326 1.0000
16.000 1.3080 0.06614 0.06042 0.0096 0.1262 1.0000
16.250 1.2972 0.07050 0.06480 0.0085 0.1205 1.0000
16.500 1.2907 0.07445 0.06884 0.0074 0.1146 1.0000
17.000 1.2753 0.08288 0.07738 0.0048 0.1040 1.0000
17.250 1.2663 0.08740 0.08193 0.0032 0.0990 1.0000
17.500 1.2614 0.09141 0.08603 0.0018 0.0939 1.0000
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