EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 344 AIRFOIL (e344-il) Reynolds number: 100,000 Max Cl/Cd: 31.46 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e344-il-100000.txt Download as CSV file: xf-e344-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 344 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2593 0.09986 0.09563 -0.0369 1.0000 0.0805
-8.750 -0.2714 0.09734 0.09324 -0.0394 1.0000 0.0822
-8.500 -0.2943 0.09491 0.09099 -0.0426 1.0000 0.0829
-8.250 -0.3184 0.09368 0.08998 -0.0410 1.0000 0.0830
-8.000 -0.3289 0.09025 0.08631 -0.0529 0.9636 0.0837
-7.750 -0.2653 0.08258 0.07896 -0.0497 0.9643 0.0881
-7.500 -0.2400 0.07730 0.07361 -0.0574 0.9364 0.0930
-7.250 -0.2482 0.07457 0.07025 -0.0688 0.9026 0.0987
-7.000 -0.2046 0.06657 0.06246 -0.0719 0.8832 0.1023
-6.750 -0.1822 0.06318 0.05891 -0.0738 0.8562 0.1078
-6.500 -0.1997 0.06355 0.05854 -0.0732 0.8309 0.1153
-6.250 -0.1726 0.05744 0.05267 -0.0738 0.8106 0.1190
-6.000 -0.1600 0.05521 0.05029 -0.0728 0.7913 0.1256
-5.750 -0.1587 0.05297 0.04774 -0.0713 0.7752 0.1348
-5.500 -0.1435 0.05067 0.04538 -0.0700 0.7593 0.1416
-5.250 -0.1362 0.04848 0.04296 -0.0683 0.7459 0.1537
-5.000 -0.1271 0.04663 0.04088 -0.0664 0.7330 0.1696
-4.750 -0.1164 0.04475 0.03889 -0.0645 0.7198 0.1869
-4.500 -0.1032 0.04272 0.03682 -0.0626 0.7083 0.2064
-4.000 -0.0791 0.03919 0.03320 -0.0582 0.6867 0.2622
-3.750 -0.0667 0.03733 0.03128 -0.0558 0.6777 0.2941
-3.500 -0.0023 0.03241 0.02395 -0.0554 0.6697 0.0804
-3.250 0.0244 0.03115 0.02190 -0.0531 0.6619 0.0705
-3.000 0.0489 0.02905 0.01965 -0.0522 0.6520 0.0688
-2.750 0.0772 0.02735 0.01766 -0.0515 0.6448 0.0668
-2.500 0.1040 0.02611 0.01626 -0.0507 0.6353 0.0660
-2.250 0.1350 0.02494 0.01481 -0.0503 0.6287 0.0674
-2.000 0.1611 0.02414 0.01395 -0.0496 0.6195 0.0715
-1.750 0.4291 0.01986 0.01221 -0.0864 0.6025 1.0000
-1.500 0.4504 0.01994 0.01200 -0.0855 0.5963 1.0000
-1.250 0.4710 0.02011 0.01202 -0.0846 0.5896 1.0000
-1.000 0.4919 0.02025 0.01200 -0.0836 0.5828 1.0000
-0.750 0.5141 0.02040 0.01190 -0.0828 0.5779 1.0000
-0.500 0.5342 0.02069 0.01215 -0.0819 0.5717 1.0000
-0.250 0.5554 0.02091 0.01226 -0.0810 0.5660 1.0000
0.000 0.5779 0.02111 0.01226 -0.0802 0.5616 1.0000
0.250 0.5978 0.02146 0.01259 -0.0793 0.5559 1.0000
0.500 0.6185 0.02177 0.01284 -0.0783 0.5504 1.0000
0.750 0.6408 0.02202 0.01296 -0.0775 0.5462 1.0000
1.000 0.6623 0.02239 0.01324 -0.0767 0.5423 1.0000
1.250 0.6807 0.02290 0.01381 -0.0755 0.5368 1.0000
1.500 0.7016 0.02325 0.01411 -0.0746 0.5322 1.0000
1.750 0.7243 0.02351 0.01425 -0.0738 0.5285 1.0000
2.000 0.7433 0.02409 0.01484 -0.0727 0.5243 1.0000
2.250 0.7602 0.02478 0.01561 -0.0714 0.5195 1.0000
2.500 0.7804 0.02522 0.01601 -0.0703 0.5154 1.0000
2.750 0.8028 0.02552 0.01623 -0.0695 0.5119 1.0000
3.000 0.8203 0.02623 0.01697 -0.0681 0.5081 1.0000
3.250 0.8326 0.02725 0.01813 -0.0663 0.5033 1.0000
3.500 0.8502 0.02789 0.01878 -0.0649 0.4994 1.0000
3.750 0.8723 0.02823 0.01906 -0.0640 0.4961 1.0000
4.000 0.8941 0.02870 0.01947 -0.0631 0.4930 1.0000
4.250 0.8948 0.03042 0.02146 -0.0599 0.4878 1.0000
4.500 0.9066 0.03141 0.02252 -0.0579 0.4835 1.0000
4.750 0.9275 0.03180 0.02288 -0.0568 0.4802 1.0000
5.000 0.9536 0.03198 0.02297 -0.0563 0.4775 1.0000
5.250 0.9391 0.03460 0.02587 -0.0515 0.4720 1.0000
5.500 0.9375 0.03633 0.02772 -0.0480 0.4673 1.0000
5.750 0.9573 0.03670 0.02810 -0.0467 0.4640 1.0000
6.000 0.9898 0.03647 0.02779 -0.0468 0.4616 1.0000
6.250 0.8948 0.04346 0.03517 -0.0338 0.4532 1.0000
6.500 0.8772 0.04575 0.03751 -0.0288 0.4485 1.0000
6.750 0.9295 0.04423 0.03594 -0.0304 0.4464 1.0000
7.000 0.9872 0.04267 0.03432 -0.0330 0.4448 1.0000
7.250 0.6731 0.06449 0.05627 -0.0093 0.4288 1.0000
7.500 0.5902 0.07439 0.06619 -0.0084 0.4235 1.0000
7.750 0.5739 0.07861 0.07044 -0.0082 0.4208 1.0000
8.000 0.6181 0.07725 0.06907 -0.0072 0.4140 1.0000
8.250 0.6176 0.08029 0.07212 -0.0068 0.4098 1.0000
8.500 0.5953 0.08553 0.07741 -0.0073 0.4086 1.0000
8.750 0.5881 0.08966 0.08157 -0.0078 0.4087 1.0000
9.000 0.5981 0.09296 0.08490 -0.0083 0.4104 1.0000
9.250 0.6160 0.09591 0.08789 -0.0088 0.4114 1.0000
9.500 0.6172 0.09640 0.08837 -0.0075 0.3941 1.0000
9.750 0.6304 0.09966 0.09168 -0.0081 0.3952 1.0000
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Polar data table (+)
Polar graphs
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