EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 343 AIRFOIL (e343-il) Reynolds number: 100,000 Max Cl/Cd: 30.84 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e343-il-100000.txt Download as CSV file: xf-e343-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 343 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3232 0.11804 0.11336 -0.0310 1.0000 0.0718
-10.250 -0.3348 0.11535 0.11076 -0.0351 1.0000 0.0722
-10.000 -0.3453 0.11215 0.10763 -0.0391 1.0000 0.0724
-9.750 -0.3005 0.10640 0.10189 -0.0306 1.0000 0.0757
-9.500 -0.2952 0.10332 0.09886 -0.0309 1.0000 0.0777
-9.250 -0.2943 0.10016 0.09577 -0.0319 1.0000 0.0802
-9.000 -0.2968 0.09701 0.09271 -0.0336 1.0000 0.0821
-8.750 -0.2195 0.08573 0.08208 -0.0364 1.0000 0.0900
-8.500 -0.2217 0.08303 0.07953 -0.0359 1.0000 0.0924
-8.250 -0.2218 0.07909 0.07571 -0.0395 0.9864 0.0958
-8.000 -0.2330 0.07241 0.06902 -0.0503 0.9573 0.0991
-7.750 -0.3959 0.08366 0.07981 -0.0398 0.9849 0.0863
-7.500 -0.3421 0.07747 0.07387 -0.0408 0.9768 0.0908
-7.250 -0.3188 0.07226 0.06850 -0.0486 0.9419 0.0973
-7.000 -0.3088 0.06705 0.06289 -0.0557 0.9136 0.1025
-6.750 -0.2696 0.06220 0.05807 -0.0589 0.8879 0.1088
-6.500 -0.2755 0.06072 0.05591 -0.0591 0.8585 0.1182
-6.250 -0.2482 0.05604 0.05141 -0.0595 0.8331 0.1245
-6.000 -0.2518 0.05491 0.04975 -0.0572 0.8115 0.1358
-5.750 -0.2309 0.05147 0.04642 -0.0565 0.7917 0.1442
-5.500 -0.2240 0.04926 0.04402 -0.0545 0.7742 0.1589
-5.250 -0.2163 0.04725 0.04184 -0.0523 0.7580 0.1754
-5.000 -0.2063 0.04525 0.03972 -0.0501 0.7431 0.1941
-4.750 -0.1949 0.04338 0.03775 -0.0479 0.7298 0.2152
-4.000 -0.1212 0.03396 0.02587 -0.0412 0.6980 0.0888
-3.750 -0.0942 0.03130 0.02262 -0.0389 0.6864 0.0693
-3.500 -0.0682 0.02906 0.01985 -0.0373 0.6765 0.0631
-3.250 -0.0412 0.02809 0.01838 -0.0358 0.6663 0.0606
-3.000 -0.0129 0.02641 0.01651 -0.0353 0.6564 0.0615
-2.750 0.0159 0.02510 0.01517 -0.0352 0.6472 0.0660
-2.500 0.0452 0.02413 0.01407 -0.0348 0.6374 0.0697
-2.250 0.0760 0.02291 0.01278 -0.0346 0.6291 0.0746
-2.000 0.3638 0.01995 0.01213 -0.0743 0.6089 1.0000
-1.750 0.3840 0.02000 0.01207 -0.0735 0.5999 1.0000
-1.500 0.4052 0.02005 0.01187 -0.0726 0.5932 1.0000
-1.250 0.4261 0.02018 0.01188 -0.0718 0.5862 1.0000
-1.000 0.4472 0.02031 0.01188 -0.0710 0.5794 1.0000
-0.750 0.4691 0.02044 0.01180 -0.0702 0.5742 1.0000
-0.500 0.4900 0.02067 0.01198 -0.0694 0.5675 1.0000
-0.250 0.5114 0.02085 0.01205 -0.0686 0.5613 1.0000
0.000 0.5337 0.02102 0.01204 -0.0678 0.5564 1.0000
0.250 0.5545 0.02135 0.01236 -0.0670 0.5506 1.0000
0.500 0.5757 0.02164 0.01261 -0.0662 0.5451 1.0000
0.750 0.5979 0.02187 0.01272 -0.0654 0.5406 1.0000
1.000 0.6196 0.02220 0.01297 -0.0646 0.5360 1.0000
1.250 0.6396 0.02262 0.01344 -0.0637 0.5301 1.0000
1.500 0.6611 0.02294 0.01371 -0.0629 0.5254 1.0000
1.750 0.6837 0.02323 0.01390 -0.0621 0.5218 1.0000
2.000 0.7036 0.02378 0.01447 -0.0612 0.5173 1.0000
2.250 0.7226 0.02433 0.01509 -0.0602 0.5119 1.0000
2.500 0.7439 0.02469 0.01542 -0.0593 0.5075 1.0000
2.750 0.7665 0.02500 0.01564 -0.0585 0.5041 1.0000
3.000 0.7845 0.02575 0.01648 -0.0574 0.4999 1.0000
3.250 0.8008 0.02654 0.01739 -0.0560 0.4947 1.0000
3.500 0.8210 0.02701 0.01785 -0.0550 0.4906 1.0000
3.750 0.8433 0.02734 0.01811 -0.0542 0.4872 1.0000
4.000 0.8609 0.02815 0.01897 -0.0529 0.4837 1.0000
4.250 0.8706 0.02946 0.02049 -0.0510 0.4782 1.0000
4.500 0.8881 0.03009 0.02116 -0.0496 0.4738 1.0000
4.750 0.9106 0.03041 0.02143 -0.0487 0.4706 1.0000
5.000 0.9340 0.03082 0.02176 -0.0480 0.4679 1.0000
5.250 0.9274 0.03322 0.02452 -0.0444 0.4615 1.0000
5.500 0.9396 0.03419 0.02558 -0.0425 0.4569 1.0000
5.750 0.9624 0.03441 0.02578 -0.0415 0.4537 1.0000
6.000 0.9893 0.03454 0.02583 -0.0411 0.4512 1.0000
6.250 0.9553 0.03867 0.03035 -0.0348 0.4438 1.0000
6.500 0.9598 0.04001 0.03177 -0.0321 0.4392 1.0000
6.750 0.9890 0.03973 0.03147 -0.0316 0.4363 1.0000
7.000 1.0271 0.03911 0.03076 -0.0321 0.4340 1.0000
7.250 0.7655 0.05655 0.04857 -0.0081 0.4192 1.0000
7.500 0.8892 0.05042 0.04246 -0.0135 0.4191 1.0000
7.750 0.9729 0.04685 0.03889 -0.0174 0.4180 1.0000
8.000 0.6661 0.07036 0.06231 0.0001 0.4017 1.0000
8.250 0.7369 0.06638 0.05839 0.0012 0.4000 1.0000
8.500 0.5953 0.08147 0.07343 0.0018 0.3926 1.0000
8.750 0.6183 0.08181 0.07377 0.0029 0.3868 1.0000
9.000 0.6345 0.08289 0.07489 0.0040 0.3809 1.0000
9.250 0.6046 0.08866 0.08068 0.0035 0.3786 1.0000
9.500 0.5934 0.09256 0.08461 0.0034 0.3755 1.0000
9.750 0.6001 0.09496 0.08705 0.0036 0.3717 1.0000
10.000 0.6035 0.09810 0.09022 0.0034 0.3704 1.0000
10.250 0.6062 0.10144 0.09360 0.0031 0.3696 1.0000
10.500 0.6157 0.10448 0.09668 0.0029 0.3685 1.0000
10.750 0.6084 0.11178 0.10405 0.0007 0.3827 1.0000
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Polar data table (+)
Polar graphs
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