EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 555 AIRFOIL (e555-il) Reynolds number: 200,000 Max Cl/Cd: 69.12 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e555-il-200000.txt Download as CSV file: xf-e555-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 555 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5249 0.10167 0.09786 -0.0529 1.0000 0.0287
-13.000 -0.5568 0.09118 0.08729 -0.0590 1.0000 0.0276
-12.750 -0.6720 0.07221 0.06767 -0.0726 1.0000 0.0251
-12.500 -0.6695 0.06888 0.06432 -0.0725 1.0000 0.0244
-12.250 -0.6803 0.06491 0.06027 -0.0733 1.0000 0.0241
-12.000 -0.6952 0.06080 0.05605 -0.0741 1.0000 0.0237
-11.750 -0.7111 0.05698 0.05209 -0.0744 1.0000 0.0235
-11.500 -0.7259 0.05358 0.04855 -0.0740 1.0000 0.0231
-11.250 -0.7414 0.05045 0.04526 -0.0730 1.0000 0.0227
-11.000 -0.7606 0.04754 0.04217 -0.0709 1.0000 0.0223
-10.750 -0.7825 0.04536 0.03983 -0.0674 1.0000 0.0220
-10.500 -0.8031 0.04293 0.03715 -0.0636 1.0000 0.0216
-10.250 -0.8194 0.04035 0.03416 -0.0599 1.0000 0.0210
-10.000 -0.8198 0.03845 0.03205 -0.0571 1.0000 0.0209
-9.750 -0.8163 0.03668 0.03012 -0.0546 1.0000 0.0209
-9.500 -0.8099 0.03503 0.02836 -0.0523 1.0000 0.0211
-9.250 -0.8023 0.03358 0.02683 -0.0501 1.0000 0.0213
-9.000 -0.7938 0.03229 0.02546 -0.0480 1.0000 0.0216
-8.750 -0.7812 0.03107 0.02417 -0.0464 0.9996 0.0221
-8.500 -0.7466 0.02953 0.02254 -0.0485 0.9958 0.0228
-8.250 -0.7126 0.02816 0.02106 -0.0505 0.9916 0.0241
-8.000 -0.6806 0.02663 0.01954 -0.0526 0.9865 0.0260
-7.750 -0.6447 0.02558 0.01843 -0.0556 0.9818 0.0295
-7.500 -0.6140 0.02395 0.01687 -0.0581 0.9754 0.0329
-7.250 -0.5798 0.02226 0.01517 -0.0614 0.9701 0.0388
-7.000 -0.5463 0.02074 0.01366 -0.0643 0.9635 0.0522
-6.750 -0.5070 0.01837 0.01157 -0.0695 0.9598 0.0950
-6.500 -0.4787 0.01521 0.00956 -0.0740 0.9524 0.2854
-6.250 -0.4368 0.01508 0.00973 -0.0771 0.9479 0.4012
-6.000 -0.3998 0.01546 0.00996 -0.0787 0.9417 0.4315
-5.750 -0.3622 0.01581 0.01024 -0.0802 0.9357 0.4488
-5.500 -0.3192 0.01610 0.01041 -0.0827 0.9324 0.4637
-5.250 -0.2871 0.01651 0.01088 -0.0828 0.9250 0.4739
-5.000 -0.2481 0.01671 0.01104 -0.0845 0.9203 0.4845
-4.750 -0.2039 0.01677 0.01093 -0.0874 0.9175 0.4960
-4.500 -0.1690 0.01725 0.01154 -0.0877 0.9116 0.5043
-4.250 -0.1302 0.01720 0.01138 -0.0897 0.9058 0.5139
-4.000 -0.0875 0.01701 0.01116 -0.0922 0.9021 0.5178
-3.750 -0.0522 0.01677 0.01085 -0.0936 0.8947 0.5220
-3.500 -0.0123 0.01632 0.01021 -0.0964 0.8882 0.5273
-3.250 0.0256 0.01595 0.00975 -0.0985 0.8814 0.5305
-3.000 0.0595 0.01573 0.00949 -0.0995 0.8724 0.5332
-2.750 0.0928 0.01555 0.00925 -0.1005 0.8633 0.5366
-2.500 0.1277 0.01529 0.00887 -0.1020 0.8544 0.5404
-2.250 0.1578 0.01505 0.00847 -0.1027 0.8432 0.5445
-2.000 0.1898 0.01484 0.00822 -0.1035 0.8338 0.5473
-1.750 0.2189 0.01473 0.00808 -0.1036 0.8230 0.5501
-1.500 0.2470 0.01463 0.00792 -0.1036 0.8118 0.5534
-1.250 0.2781 0.01449 0.00768 -0.1042 0.8021 0.5570
-1.000 0.3074 0.01436 0.00742 -0.1047 0.7910 0.5609
-0.750 0.3346 0.01426 0.00730 -0.1045 0.7798 0.5638
-0.500 0.3639 0.01422 0.00722 -0.1046 0.7699 0.5669
-0.250 0.3913 0.01417 0.00714 -0.1045 0.7587 0.5704
0.000 0.4189 0.01413 0.00703 -0.1045 0.7476 0.5742
0.250 0.4489 0.01408 0.00686 -0.1050 0.7377 0.5782
0.500 0.4752 0.01402 0.00683 -0.1046 0.7265 0.5810
0.750 0.5019 0.01403 0.00684 -0.1043 0.7156 0.5845
1.000 0.5307 0.01404 0.00679 -0.1045 0.7058 0.5887
1.250 0.5579 0.01404 0.00674 -0.1044 0.6944 0.5931
1.500 0.5847 0.01403 0.00673 -0.1042 0.6835 0.5965
1.750 0.6126 0.01406 0.00674 -0.1041 0.6736 0.5999
2.000 0.6388 0.01410 0.00679 -0.1038 0.6622 0.6042
2.250 0.6660 0.01416 0.00682 -0.1037 0.6511 0.6093
2.500 0.6936 0.01419 0.00683 -0.1036 0.6410 0.6133
2.750 0.7192 0.01424 0.00692 -0.1031 0.6294 0.6172
3.000 0.7454 0.01431 0.00701 -0.1028 0.6180 0.6219
3.250 0.7730 0.01440 0.00703 -0.1028 0.6069 0.6273
3.500 0.7987 0.01445 0.00713 -0.1023 0.5956 0.6315
3.750 0.8236 0.01453 0.00727 -0.1017 0.5834 0.6368
4.000 0.8501 0.01465 0.00736 -0.1014 0.5717 0.6429
4.250 0.8759 0.01474 0.00747 -0.1010 0.5605 0.6475
4.500 0.9006 0.01484 0.00762 -0.1004 0.5482 0.6532
4.750 0.9258 0.01497 0.00777 -0.0999 0.5356 0.6599
5.000 0.9500 0.01508 0.00796 -0.0991 0.5236 0.6656
5.250 0.9751 0.01524 0.00811 -0.0986 0.5115 0.6730
5.500 0.9993 0.01538 0.00829 -0.0979 0.4991 0.6797
5.750 1.0224 0.01552 0.00852 -0.0970 0.4858 0.6871
6.000 1.0458 0.01568 0.00874 -0.0962 0.4727 0.6949
6.250 1.0686 0.01586 0.00898 -0.0952 0.4595 0.7035
6.500 1.0909 0.01605 0.00922 -0.0942 0.4458 0.7127
6.750 1.1128 0.01627 0.00947 -0.0932 0.4319 0.7235
7.000 1.1332 0.01648 0.00975 -0.0918 0.4174 0.7335
7.250 1.1532 0.01671 0.01004 -0.0903 0.4021 0.7451
7.500 1.1722 0.01696 0.01036 -0.0888 0.3862 0.7585
7.750 1.1901 0.01722 0.01071 -0.0870 0.3697 0.7736
8.000 1.2063 0.01750 0.01108 -0.0849 0.3527 0.7907
8.250 1.2207 0.01779 0.01147 -0.0825 0.3349 0.8110
8.500 1.2330 0.01810 0.01188 -0.0797 0.3166 0.8377
8.750 1.2390 0.01833 0.01222 -0.0756 0.2993 0.8817
9.000 1.2466 0.01862 0.01255 -0.0722 0.2808 1.0000
9.250 1.2592 0.01935 0.01317 -0.0702 0.2599 1.0000
9.500 1.2701 0.02013 0.01389 -0.0679 0.2386 1.0000
9.750 1.2782 0.02106 0.01471 -0.0654 0.2189 1.0000
10.000 1.2852 0.02210 0.01567 -0.0628 0.2007 1.0000
10.250 1.2924 0.02318 0.01670 -0.0604 0.1833 1.0000
10.500 1.2984 0.02437 0.01785 -0.0580 0.1676 1.0000
10.750 1.3034 0.02568 0.01912 -0.0556 0.1536 1.0000
11.000 1.3072 0.02714 0.02053 -0.0534 0.1409 1.0000
11.250 1.3096 0.02877 0.02211 -0.0512 0.1295 1.0000
11.500 1.3146 0.03032 0.02371 -0.0495 0.1185 1.0000
11.750 1.3180 0.03207 0.02548 -0.0478 0.1087 1.0000
12.000 1.3181 0.03416 0.02753 -0.0461 0.1007 1.0000
12.250 1.3213 0.03609 0.02951 -0.0448 0.0926 1.0000
12.500 1.3223 0.03831 0.03177 -0.0436 0.0857 1.0000
12.750 1.3227 0.04066 0.03412 -0.0426 0.0795 1.0000
13.000 1.3237 0.04309 0.03662 -0.0417 0.0738 1.0000
13.250 1.3240 0.04564 0.03921 -0.0411 0.0688 1.0000
13.500 1.3228 0.04845 0.04206 -0.0405 0.0644 1.0000
13.750 1.3242 0.05110 0.04482 -0.0402 0.0600 1.0000
14.000 1.3214 0.05424 0.04791 -0.0399 0.0566 1.0000
14.250 1.3229 0.05707 0.05091 -0.0398 0.0531 1.0000
14.500 1.3231 0.06011 0.05402 -0.0400 0.0500 1.0000
14.750 1.3219 0.06330 0.05712 -0.0399 0.0471 1.0000
15.000 1.3226 0.06652 0.06056 -0.0404 0.0448 1.0000
15.250 1.3226 0.06984 0.06398 -0.0409 0.0423 1.0000
15.500 1.3221 0.07323 0.06737 -0.0416 0.0402 1.0000
15.750 1.3227 0.07657 0.07081 -0.0419 0.0382 1.0000
16.000 1.3219 0.08029 0.07469 -0.0429 0.0364 1.0000
16.250 1.3214 0.08394 0.07843 -0.0439 0.0347 1.0000
16.500 1.3230 0.08719 0.08165 -0.0447 0.0330 1.0000
16.750 1.3216 0.09114 0.08576 -0.0457 0.0316 1.0000
17.000 1.3177 0.09561 0.09042 -0.0474 0.0304 1.0000
17.250 1.3151 0.09987 0.09481 -0.0491 0.0292 1.0000
17.500 1.3150 0.10368 0.09867 -0.0506 0.0280 1.0000
17.750 1.3198 0.10649 0.10143 -0.0510 0.0267 1.0000
18.000 1.3108 0.11215 0.10734 -0.0539 0.0261 1.0000
18.250 1.3020 0.11784 0.11326 -0.0569 0.0254 1.0000
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