EPPLER 864 STRUT AIRFOIL (e864-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 864 STRUT AIRFOIL (e864-il) Reynolds number: 200,000 Max Cl/Cd: 15 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e864-il-200000-n5.txt Download as CSV file: xf-e864-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 864 STRUT 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2932 0.10835 0.10017 -0.0338 0.5174 0.2788
-12.750 -0.2700 0.10797 0.09977 -0.0346 0.5138 0.2796
-12.500 -0.3008 0.10111 0.09283 -0.0352 0.5128 0.2907
-12.250 -0.2762 0.10092 0.09260 -0.0360 0.5094 0.2912
-12.000 -0.2518 0.10070 0.09233 -0.0367 0.5063 0.2918
-11.750 -0.2281 0.10041 0.09199 -0.0375 0.5035 0.2926
-11.500 -0.2617 0.09348 0.08496 -0.0378 0.5028 0.3040
-11.250 -0.2364 0.09332 0.08482 -0.0386 0.5005 0.3044
-11.000 -0.2114 0.09313 0.08463 -0.0393 0.4981 0.3050
-10.750 -0.1870 0.09286 0.08437 -0.0401 0.4957 0.3057
-10.500 -0.1636 0.09248 0.08399 -0.0408 0.4933 0.3066
-10.250 -0.1419 0.09190 0.08339 -0.0415 0.4911 0.3078
-10.000 -0.1233 0.09097 0.08244 -0.0422 0.4890 0.3095
-9.250 -0.1631 0.07806 0.06935 -0.0425 0.4855 0.3317
-9.000 -0.1373 0.07799 0.06924 -0.0432 0.4833 0.3323
-8.750 -0.1123 0.07785 0.06905 -0.0439 0.4811 0.3329
-8.500 -0.0882 0.07758 0.06878 -0.0445 0.4792 0.3337
-8.250 -0.0656 0.07711 0.06833 -0.0452 0.4774 0.3347
-8.000 -0.0450 0.07644 0.06767 -0.0457 0.4757 0.3361
-7.750 -0.0306 0.07519 0.06642 -0.0462 0.4742 0.3388
-7.500 -0.4909 0.03529 0.02577 -0.0283 0.4811 0.3913
-7.250 -0.4596 0.03535 0.02586 -0.0293 0.4791 0.3922
-7.000 -0.4302 0.03534 0.02590 -0.0301 0.4771 0.3932
-6.750 -0.4031 0.03526 0.02586 -0.0307 0.4753 0.3943
-6.500 -0.3802 0.03500 0.02562 -0.0310 0.4735 0.3957
-6.250 -0.3660 0.03432 0.02494 -0.0306 0.4718 0.3974
-6.000 -0.3670 0.03300 0.02356 -0.0288 0.4704 0.3998
-5.750 -0.3800 0.03133 0.02178 -0.0254 0.4692 0.4024
-5.500 -0.3961 0.02982 0.02013 -0.0211 0.4680 0.4050
-5.250 -0.4158 0.02860 0.01875 -0.0154 0.4669 0.4073
-5.000 -0.4094 0.02821 0.01830 -0.0128 0.4655 0.4089
-4.750 -0.3837 0.02811 0.01822 -0.0130 0.4639 0.4100
-4.500 -0.3621 0.02802 0.01812 -0.0126 0.4623 0.4112
-4.250 -0.3435 0.02794 0.01800 -0.0116 0.4607 0.4123
-4.000 -0.3258 0.02787 0.01788 -0.0105 0.4591 0.4135
-3.750 -0.3081 0.02773 0.01776 -0.0095 0.4577 0.4149
-3.500 -0.2907 0.02759 0.01764 -0.0084 0.4564 0.4163
-3.250 -0.2739 0.02746 0.01751 -0.0072 0.4550 0.4179
-3.000 -0.2575 0.02731 0.01734 -0.0059 0.4536 0.4196
-2.750 -0.2413 0.02714 0.01714 -0.0046 0.4522 0.4213
-2.500 -0.2248 0.02695 0.01691 -0.0034 0.4507 0.4229
-2.250 -0.2077 0.02677 0.01667 -0.0022 0.4492 0.4243
-2.000 -0.1903 0.02660 0.01642 -0.0010 0.4477 0.4256
-1.750 -0.1672 0.02646 0.01627 -0.0008 0.4462 0.4269
-1.500 -0.1407 0.02639 0.01623 -0.0011 0.4446 0.4282
-1.250 -0.1153 0.02636 0.01620 -0.0012 0.4432 0.4295
-1.000 -0.0903 0.02635 0.01619 -0.0012 0.4420 0.4308
-0.750 -0.0651 0.02635 0.01617 -0.0013 0.4408 0.4320
-0.500 -0.0399 0.02638 0.01617 -0.0014 0.4396 0.4333
-0.250 -0.0166 0.02642 0.01622 -0.0012 0.4384 0.4347
0.000 0.0045 0.02644 0.01629 -0.0006 0.4370 0.4361
0.250 0.0253 0.02648 0.01636 0.0000 0.4354 0.4376
0.500 0.0460 0.02651 0.01641 0.0007 0.4338 0.4393
0.750 0.0668 0.02655 0.01645 0.0013 0.4322 0.4409
1.000 0.0878 0.02658 0.01647 0.0019 0.4308 0.4424
1.250 0.1091 0.02662 0.01649 0.0024 0.4294 0.4437
1.500 0.1305 0.02665 0.01649 0.0030 0.4280 0.4449
1.750 0.1538 0.02665 0.01649 0.0032 0.4266 0.4462
2.000 0.1782 0.02664 0.01651 0.0032 0.4252 0.4475
2.250 0.2028 0.02665 0.01655 0.0032 0.4239 0.4489
2.500 0.2276 0.02670 0.01660 0.0032 0.4227 0.4504
2.750 0.2531 0.02678 0.01668 0.0031 0.4215 0.4519
3.000 0.2800 0.02692 0.01679 0.0027 0.4204 0.4535
3.250 0.2956 0.02716 0.01710 0.0041 0.4191 0.4549
3.500 0.3068 0.02744 0.01747 0.0061 0.4176 0.4563
3.750 0.3165 0.02773 0.01783 0.0084 0.4159 0.4577
4.000 0.3249 0.02802 0.01817 0.0109 0.4141 0.4591
4.250 0.3286 0.02827 0.01847 0.0142 0.4123 0.4605
4.500 0.3349 0.02855 0.01877 0.0169 0.4106 0.4619
4.750 0.3461 0.02884 0.01907 0.0187 0.4090 0.4633
5.000 0.3628 0.02910 0.01931 0.0197 0.4075 0.4648
5.250 0.3839 0.02925 0.01944 0.0200 0.4061 0.4664
5.500 0.4092 0.02926 0.01947 0.0198 0.4047 0.4682
5.750 0.4385 0.02923 0.01942 0.0190 0.4033 0.4700
6.000 0.4395 0.03007 0.02036 0.0216 0.4012 0.4714
6.250 0.3933 0.03286 0.02340 0.0285 0.3974 0.4722
6.500 0.3529 0.03628 0.02698 0.0332 0.3931 0.4730
6.750 0.3580 0.03757 0.02832 0.0340 0.3906 0.4745
7.000 0.3821 0.03777 0.02851 0.0335 0.3892 0.4763
7.250 0.4122 0.03761 0.02833 0.0327 0.3881 0.4783
7.500 0.4444 0.03737 0.02805 0.0318 0.3871 0.4804
7.750 0.4788 0.03704 0.02767 0.0307 0.3862 0.4826
8.000 0.0991 0.07091 0.06214 0.0446 0.3429 0.4767
8.250 0.0649 0.07709 0.06839 0.0452 0.3324 0.4774
8.500 0.0854 0.07774 0.06904 0.0446 0.3307 0.4792
8.750 0.1084 0.07814 0.06943 0.0439 0.3295 0.4811
9.000 0.1322 0.07847 0.06975 0.0433 0.3287 0.4831
9.250 0.1046 0.08428 0.07562 0.0435 0.3191 0.4838
9.500 0.1238 0.08511 0.07644 0.0428 0.3172 0.4856
10.250 0.1528 0.09068 0.08213 0.0412 0.3066 0.4911
10.500 0.1681 0.09197 0.08346 0.0406 0.3041 0.4932
10.750 0.1887 0.09265 0.08419 0.0399 0.3027 0.4956
11.000 0.2112 0.09313 0.08469 0.0391 0.3017 0.4981
11.250 0.2352 0.09343 0.08501 0.0384 0.3009 0.5007
11.500 0.2606 0.09356 0.08515 0.0376 0.3003 0.5034
11.750 0.2869 0.09358 0.08516 0.0368 0.2997 0.5062
12.000 0.2594 0.09981 0.09145 0.0364 0.2885 0.5072
12.250 0.2833 0.10011 0.09175 0.0356 0.2877 0.5097
12.500 0.2922 0.10217 0.09386 0.0349 0.2842 0.5120
12.750 0.3281 0.10102 0.09275 0.0340 0.2856 0.5155
13.000 0.3066 0.10674 0.09856 0.0334 0.2756 0.5170
13.250 0.3296 0.10713 0.09899 0.0326 0.2746 0.5205
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