EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 555 AIRFOIL (e555-il) Reynolds number: 500,000 Max Cl/Cd: 86.45 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e555-il-500000-n5.txt Download as CSV file: xf-e555-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.6810 0.13869 0.13572 -0.0289 1.0000 0.0046
-17.500 -0.7182 0.12558 0.12241 -0.0351 1.0000 0.0045
-17.250 -0.7351 0.11762 0.11430 -0.0390 1.0000 0.0045
-17.000 -0.7538 0.10968 0.10621 -0.0429 1.0000 0.0045
-16.750 -0.7636 0.10367 0.10009 -0.0458 1.0000 0.0044
-16.500 -0.7760 0.09746 0.09375 -0.0488 1.0000 0.0044
-16.250 -0.7911 0.09103 0.08719 -0.0518 1.0000 0.0045
-16.000 -0.7998 0.08591 0.08196 -0.0542 1.0000 0.0044
-15.750 -0.8058 0.08138 0.07733 -0.0562 1.0000 0.0044
-15.500 -0.8147 0.07660 0.07243 -0.0581 1.0000 0.0044
-15.250 -0.8163 0.07298 0.06872 -0.0596 1.0000 0.0044
-15.000 -0.8252 0.06857 0.06419 -0.0612 1.0000 0.0044
-14.750 -0.8309 0.06473 0.06025 -0.0624 1.0000 0.0045
-14.500 -0.8327 0.06152 0.05695 -0.0633 1.0000 0.0045
-14.250 -0.8359 0.05826 0.05361 -0.0641 1.0000 0.0045
-14.000 -0.8381 0.05526 0.05052 -0.0647 1.0000 0.0045
-13.750 -0.8405 0.05237 0.04756 -0.0652 1.0000 0.0046
-13.500 -0.8402 0.04991 0.04502 -0.0653 1.0000 0.0046
-13.250 -0.8429 0.04732 0.04236 -0.0653 1.0000 0.0046
-13.000 -0.8425 0.04510 0.04007 -0.0652 1.0000 0.0046
-12.750 -0.8437 0.04283 0.03774 -0.0648 1.0000 0.0047
-12.500 -0.8443 0.04071 0.03556 -0.0643 1.0000 0.0047
-12.250 -0.8446 0.03875 0.03354 -0.0636 1.0000 0.0047
-12.000 -0.8461 0.03680 0.03153 -0.0626 1.0000 0.0047
-11.750 -0.8481 0.03496 0.02965 -0.0613 1.0000 0.0048
-11.500 -0.8503 0.03329 0.02793 -0.0598 1.0000 0.0049
-11.250 -0.8465 0.03155 0.02614 -0.0595 0.9993 0.0049
-11.000 -0.8258 0.02956 0.02407 -0.0626 0.9963 0.0050
-10.750 -0.8049 0.02768 0.02212 -0.0656 0.9926 0.0052
-10.500 -0.7864 0.02587 0.02023 -0.0679 0.9871 0.0053
-10.250 -0.7688 0.02414 0.01842 -0.0700 0.9800 0.0054
-9.750 -0.7236 0.02084 0.01495 -0.0751 0.9643 0.0058
-9.500 -0.6951 0.01967 0.01368 -0.0775 0.9597 0.0061
-9.250 -0.6729 0.01864 0.01258 -0.0782 0.9511 0.0063
-9.000 -0.6425 0.01762 0.01151 -0.0804 0.9468 0.0067
-8.750 -0.6145 0.01683 0.01066 -0.0817 0.9399 0.0073
-8.500 -0.5814 0.01606 0.00982 -0.0838 0.9348 0.0079
-8.250 -0.5440 0.01528 0.00899 -0.0868 0.9309 0.0091
-8.000 -0.5101 0.01466 0.00831 -0.0890 0.9233 0.0106
-7.750 -0.4691 0.01399 0.00761 -0.0926 0.9179 0.0137
-7.500 -0.4311 0.01339 0.00700 -0.0955 0.9099 0.0188
-7.250 -0.3923 0.01281 0.00641 -0.0986 0.9011 0.0273
-7.000 -0.3580 0.01226 0.00588 -0.1007 0.8901 0.0399
-6.750 -0.3258 0.01168 0.00535 -0.1024 0.8789 0.0618
-6.500 -0.2957 0.01107 0.00483 -0.1037 0.8674 0.0932
-6.250 -0.2688 0.01045 0.00434 -0.1043 0.8548 0.1352
-6.000 -0.2439 0.00946 0.00366 -0.1050 0.8423 0.2197
-5.750 -0.2183 0.00858 0.00316 -0.1056 0.8301 0.3249
-5.500 -0.1901 0.00842 0.00301 -0.1059 0.8183 0.3568
-5.250 -0.1619 0.00835 0.00290 -0.1060 0.8064 0.3759
-5.000 -0.1338 0.00832 0.00282 -0.1060 0.7950 0.3924
-4.750 -0.1056 0.00832 0.00275 -0.1061 0.7841 0.4041
-4.500 -0.0775 0.00834 0.00268 -0.1061 0.7731 0.4139
-4.250 -0.0495 0.00838 0.00268 -0.1061 0.7620 0.4265
-4.000 -0.0215 0.00842 0.00265 -0.1060 0.7515 0.4352
-3.750 0.0063 0.00843 0.00257 -0.1060 0.7407 0.4384
-3.500 0.0343 0.00843 0.00250 -0.1060 0.7301 0.4412
-3.250 0.0622 0.00845 0.00242 -0.1059 0.7196 0.4440
-3.000 0.0900 0.00847 0.00234 -0.1059 0.7089 0.4463
-2.750 0.1179 0.00847 0.00228 -0.1059 0.6983 0.4485
-2.500 0.1456 0.00847 0.00224 -0.1058 0.6882 0.4509
-2.250 0.1733 0.00849 0.00221 -0.1058 0.6776 0.4535
-2.000 0.2011 0.00851 0.00217 -0.1057 0.6676 0.4561
-1.750 0.2287 0.00855 0.00214 -0.1056 0.6575 0.4585
-1.500 0.2566 0.00858 0.00211 -0.1056 0.6472 0.4609
-1.250 0.2845 0.00863 0.00209 -0.1056 0.6377 0.4632
-1.000 0.3119 0.00865 0.00209 -0.1055 0.6277 0.4656
-0.750 0.3397 0.00868 0.00209 -0.1055 0.6180 0.4682
-0.500 0.3672 0.00873 0.00211 -0.1054 0.6087 0.4708
-0.250 0.3949 0.00878 0.00212 -0.1053 0.5986 0.4734
0.000 0.4225 0.00883 0.00214 -0.1053 0.5891 0.4759
0.250 0.4499 0.00891 0.00216 -0.1052 0.5794 0.4784
0.500 0.4775 0.00895 0.00219 -0.1051 0.5697 0.4808
0.750 0.5047 0.00902 0.00224 -0.1050 0.5602 0.4836
1.000 0.5322 0.00908 0.00229 -0.1049 0.5503 0.4864
1.250 0.5594 0.00916 0.00235 -0.1048 0.5407 0.4893
1.500 0.5864 0.00925 0.00241 -0.1046 0.5307 0.4921
1.750 0.6137 0.00934 0.00247 -0.1045 0.5204 0.4948
2.000 0.6406 0.00943 0.00255 -0.1043 0.5103 0.4974
2.250 0.6671 0.00953 0.00264 -0.1041 0.4991 0.5003
2.500 0.6940 0.00963 0.00274 -0.1039 0.4878 0.5036
2.750 0.7205 0.00975 0.00284 -0.1036 0.4767 0.5070
3.000 0.7467 0.00989 0.00295 -0.1033 0.4652 0.5101
3.250 0.7732 0.01001 0.00306 -0.1031 0.4536 0.5130
3.500 0.7994 0.01014 0.00320 -0.1028 0.4419 0.5160
3.750 0.8252 0.01029 0.00334 -0.1025 0.4301 0.5196
4.000 0.8507 0.01046 0.00349 -0.1021 0.4177 0.5235
4.250 0.8765 0.01062 0.00364 -0.1017 0.4052 0.5274
4.500 0.9021 0.01079 0.00381 -0.1013 0.3930 0.5309
4.750 0.9273 0.01097 0.00399 -0.1009 0.3805 0.5347
5.000 0.9521 0.01117 0.00419 -0.1004 0.3678 0.5388
5.250 0.9766 0.01140 0.00439 -0.0998 0.3545 0.5429
5.500 1.0009 0.01163 0.00461 -0.0992 0.3403 0.5471
5.750 1.0250 0.01186 0.00485 -0.0986 0.3258 0.5520
6.000 1.0486 0.01213 0.00510 -0.0979 0.3107 0.5573
6.500 1.0937 0.01276 0.00567 -0.0962 0.2762 0.5671
6.750 1.1157 0.01310 0.00598 -0.0953 0.2583 0.5726
7.250 1.1566 0.01392 0.00671 -0.0929 0.2192 0.5841
7.500 1.1757 0.01439 0.00712 -0.0916 0.2005 0.5910
7.750 1.1946 0.01483 0.00754 -0.0902 0.1837 0.5978
8.000 1.2118 0.01528 0.00797 -0.0884 0.1679 0.6053
8.250 1.2277 0.01577 0.00842 -0.0865 0.1521 0.6125
8.500 1.2430 0.01630 0.00893 -0.0845 0.1371 0.6204
8.750 1.2584 0.01684 0.00945 -0.0825 0.1243 0.6286
9.000 1.2735 0.01738 0.01000 -0.0806 0.1131 0.6381
9.250 1.2876 0.01798 0.01060 -0.0785 0.1021 0.6481
9.500 1.3024 0.01855 0.01119 -0.0766 0.0926 0.6594
9.750 1.3159 0.01916 0.01185 -0.0746 0.0839 0.6714
10.000 1.3280 0.01986 0.01257 -0.0725 0.0754 0.6840
10.250 1.3397 0.02059 0.01333 -0.0703 0.0677 0.6976
10.500 1.3516 0.02132 0.01412 -0.0683 0.0612 0.7131
10.750 1.3617 0.02216 0.01501 -0.0662 0.0553 0.7314
11.000 1.3723 0.02298 0.01593 -0.0642 0.0503 0.7543
11.250 1.3813 0.02389 0.01695 -0.0621 0.0460 0.7830
11.500 1.3893 0.02477 0.01799 -0.0598 0.0420 0.8269
11.750 1.3918 0.02559 0.01904 -0.0568 0.0389 1.0000
12.000 1.4011 0.02675 0.02024 -0.0552 0.0355 1.0000
12.250 1.4079 0.02814 0.02164 -0.0536 0.0325 1.0000
12.500 1.4161 0.02948 0.02303 -0.0522 0.0300 1.0000
12.750 1.4221 0.03105 0.02464 -0.0508 0.0274 1.0000
13.000 1.4285 0.03265 0.02630 -0.0496 0.0254 1.0000
13.250 1.4341 0.03439 0.02809 -0.0486 0.0235 1.0000
13.500 1.4378 0.03635 0.03010 -0.0475 0.0217 1.0000
13.750 1.4430 0.03827 0.03210 -0.0467 0.0202 1.0000
14.000 1.4464 0.04042 0.03431 -0.0460 0.0189 1.0000
14.250 1.4480 0.04283 0.03678 -0.0455 0.0177 1.0000
14.500 1.4513 0.04516 0.03920 -0.0451 0.0167 1.0000
14.750 1.4531 0.04774 0.04187 -0.0448 0.0157 1.0000
15.000 1.4531 0.05060 0.04480 -0.0448 0.0148 1.0000
15.250 1.4533 0.05356 0.04784 -0.0448 0.0140 1.0000
15.500 1.4538 0.05658 0.05096 -0.0451 0.0133 1.0000
15.750 1.4528 0.05987 0.05434 -0.0455 0.0125 1.0000
16.000 1.4505 0.06344 0.05799 -0.0462 0.0119 1.0000
16.250 1.4473 0.06725 0.06190 -0.0470 0.0113 1.0000
16.500 1.4455 0.07099 0.06574 -0.0479 0.0108 1.0000
16.750 1.4425 0.07497 0.06983 -0.0491 0.0103 1.0000
17.000 1.4384 0.07923 0.07418 -0.0504 0.0098 1.0000
17.250 1.4329 0.08381 0.07887 -0.0520 0.0094 1.0000
17.500 1.4261 0.08871 0.08388 -0.0538 0.0090 1.0000
17.750 1.4214 0.09337 0.08865 -0.0557 0.0086 1.0000
18.000 1.4159 0.09823 0.09362 -0.0577 0.0082 1.0000
18.250 1.4093 0.10337 0.09888 -0.0599 0.0079 1.0000
18.500 1.4019 0.10875 0.10437 -0.0624 0.0076 1.0000
18.750 1.3939 0.11429 0.11001 -0.0651 0.0073 1.0000
19.000 1.3851 0.12005 0.11587 -0.0680 0.0071 1.0000
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Polar data table (+)
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