EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 200,000 Max Cl/Cd: 69.24 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e655-il-200000-n5.txt Download as CSV file: xf-e655-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 655 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4578 0.05911 0.05389 -0.1211 0.8404 0.0116
-13.500 -0.4698 0.05400 0.04857 -0.1247 0.8301 0.0117
-13.250 -0.4799 0.04980 0.04418 -0.1270 0.8213 0.0118
-13.000 -0.4890 0.04616 0.04030 -0.1285 0.8132 0.0118
-12.750 -0.4947 0.04318 0.03711 -0.1292 0.8064 0.0118
-12.500 -0.4967 0.04088 0.03471 -0.1295 0.7998 0.0121
-12.250 -0.4971 0.03885 0.03252 -0.1294 0.7943 0.0123
-12.000 -0.4977 0.03675 0.03024 -0.1288 0.7894 0.0124
-11.750 -0.4958 0.03503 0.02837 -0.1281 0.7844 0.0128
-11.500 -0.4922 0.03343 0.02659 -0.1272 0.7799 0.0130
-11.250 -0.4880 0.03184 0.02481 -0.1260 0.7761 0.0132
-11.000 -0.4814 0.03050 0.02329 -0.1248 0.7720 0.0139
-10.750 -0.4738 0.02918 0.02177 -0.1234 0.7677 0.0145
-10.500 -0.4651 0.02814 0.02066 -0.1221 0.7638 0.0149
-10.250 -0.4553 0.02723 0.01965 -0.1207 0.7606 0.0155
-10.000 -0.4444 0.02640 0.01869 -0.1192 0.7577 0.0164
-9.750 -0.4339 0.02552 0.01768 -0.1175 0.7545 0.0172
-9.500 -0.4235 0.02468 0.01674 -0.1156 0.7514 0.0180
-9.250 -0.4098 0.02394 0.01595 -0.1143 0.7485 0.0188
-9.000 -0.3943 0.02320 0.01512 -0.1130 0.7459 0.0199
-8.750 -0.3772 0.02252 0.01429 -0.1119 0.7435 0.0214
-8.500 -0.3594 0.02193 0.01365 -0.1110 0.7411 0.0230
-8.250 -0.3408 0.02135 0.01297 -0.1100 0.7383 0.0253
-8.000 -0.3225 0.02074 0.01236 -0.1091 0.7356 0.0272
-7.750 -0.3025 0.02021 0.01173 -0.1082 0.7332 0.0300
-7.500 -0.2822 0.01969 0.01120 -0.1075 0.7309 0.0332
-7.250 -0.2612 0.01919 0.01065 -0.1068 0.7289 0.0369
-7.000 -0.2389 0.01878 0.01016 -0.1063 0.7270 0.0418
-6.750 -0.2167 0.01832 0.00967 -0.1058 0.7252 0.0474
-6.500 -0.1949 0.01791 0.00928 -0.1052 0.7228 0.0542
-6.250 -0.1725 0.01751 0.00890 -0.1047 0.7203 0.0625
-6.000 -0.1496 0.01714 0.00854 -0.1043 0.7181 0.0731
-5.750 -0.1262 0.01678 0.00821 -0.1039 0.7160 0.0865
-5.500 -0.1022 0.01645 0.00790 -0.1036 0.7141 0.1035
-5.250 -0.0781 0.01610 0.00761 -0.1034 0.7122 0.1243
-5.000 -0.0534 0.01577 0.00733 -0.1032 0.7105 0.1510
-4.750 -0.0286 0.01543 0.00708 -0.1032 0.7088 0.1834
-4.500 -0.0047 0.01510 0.00689 -0.1029 0.7067 0.2200
-4.250 0.0192 0.01479 0.00674 -0.1028 0.7046 0.2625
-4.000 0.0434 0.01445 0.00659 -0.1026 0.7025 0.3128
-3.750 0.0680 0.01410 0.00646 -0.1025 0.7004 0.3701
-3.500 0.0928 0.01375 0.00633 -0.1024 0.6982 0.4352
-3.250 0.1179 0.01345 0.00631 -0.1022 0.6963 0.5071
-3.000 0.1435 0.01335 0.00643 -0.1017 0.6946 0.5728
-2.750 0.1705 0.01342 0.00656 -0.1014 0.6931 0.6178
-2.500 0.1985 0.01354 0.00666 -0.1013 0.6917 0.6463
-2.250 0.2243 0.01369 0.00681 -0.1010 0.6893 0.6670
-2.000 0.2505 0.01384 0.00695 -0.1007 0.6868 0.6836
-1.750 0.2768 0.01400 0.00710 -0.1004 0.6846 0.6970
-1.500 0.3037 0.01414 0.00721 -0.1002 0.6825 0.7087
-1.250 0.3319 0.01425 0.00724 -0.1004 0.6805 0.7204
-1.000 0.3588 0.01438 0.00735 -0.1000 0.6786 0.7283
-0.750 0.3877 0.01448 0.00737 -0.1004 0.6770 0.7380
-0.500 0.4152 0.01461 0.00748 -0.1001 0.6755 0.7448
-0.250 0.4407 0.01478 0.00765 -0.0999 0.6728 0.7536
0.000 0.4646 0.01496 0.00786 -0.0992 0.6700 0.7594
0.250 0.4902 0.01510 0.00800 -0.0989 0.6674 0.7660
0.500 0.5177 0.01519 0.00806 -0.0990 0.6650 0.7728
0.750 0.5441 0.01527 0.00814 -0.0987 0.6628 0.7774
1.000 0.5725 0.01532 0.00816 -0.0988 0.6608 0.7826
1.250 0.6032 0.01535 0.00812 -0.0996 0.6590 0.7880
1.500 0.6250 0.01553 0.00837 -0.0987 0.6554 0.7915
1.750 0.6488 0.01564 0.00853 -0.0981 0.6518 0.7951
2.000 0.6754 0.01569 0.00858 -0.0981 0.6487 0.7991
2.250 0.7046 0.01569 0.00855 -0.0985 0.6460 0.8032
2.500 0.7348 0.01567 0.00849 -0.0991 0.6437 0.8067
2.750 0.7584 0.01578 0.00866 -0.0985 0.6403 0.8096
3.000 0.7805 0.01592 0.00888 -0.0977 0.6360 0.8131
3.250 0.8068 0.01596 0.00893 -0.0977 0.6324 0.8168
3.500 0.8365 0.01592 0.00888 -0.0982 0.6293 0.8203
3.750 0.8669 0.01585 0.00879 -0.0988 0.6266 0.8234
4.000 0.8838 0.01606 0.00914 -0.0971 0.6209 0.8267
4.250 0.9084 0.01609 0.00921 -0.0967 0.6164 0.8300
4.500 0.9372 0.01601 0.00914 -0.0970 0.6128 0.8333
4.750 0.9610 0.01610 0.00928 -0.0966 0.6079 0.8374
5.000 0.9813 0.01619 0.00946 -0.0954 0.6019 0.8409
5.250 1.0074 0.01610 0.00940 -0.0952 0.5973 0.8441
5.500 1.0275 0.01621 0.00959 -0.0940 0.5911 0.8479
5.750 1.0492 0.01627 0.00971 -0.0932 0.5845 0.8521
6.000 1.0740 0.01623 0.00971 -0.0927 0.5786 0.8560
6.250 1.0882 0.01639 0.00997 -0.0905 0.5703 0.8605
6.500 1.1102 0.01638 0.00999 -0.0896 0.5631 0.8651
6.750 1.1257 0.01653 0.01022 -0.0877 0.5537 0.8703
7.000 1.1381 0.01664 0.01038 -0.0850 0.5444 0.8752
7.250 1.1556 0.01669 0.01044 -0.0833 0.5345 0.8808
7.500 1.1668 0.01698 0.01078 -0.0807 0.5222 0.8878
7.750 1.1783 0.01725 0.01109 -0.0782 0.5096 0.8949
8.000 1.1911 0.01758 0.01142 -0.0760 0.4953 0.9027
8.250 1.2009 0.01797 0.01181 -0.0734 0.4802 0.9116
8.500 1.2096 0.01847 0.01229 -0.0708 0.4639 0.9228
8.750 1.2174 0.01908 0.01288 -0.0682 0.4471 0.9397
9.000 1.2271 0.01978 0.01356 -0.0665 0.4287 1.0000
9.500 1.2444 0.02198 0.01561 -0.0635 0.3922 1.0000
9.750 1.2513 0.02324 0.01681 -0.0619 0.3745 1.0000
10.000 1.2577 0.02457 0.01808 -0.0603 0.3578 1.0000
10.250 1.2636 0.02597 0.01943 -0.0588 0.3414 1.0000
10.500 1.2686 0.02746 0.02087 -0.0572 0.3248 1.0000
10.750 1.2739 0.02897 0.02234 -0.0558 0.3095 1.0000
11.000 1.2785 0.03057 0.02390 -0.0544 0.2941 1.0000
11.250 1.2832 0.03220 0.02550 -0.0531 0.2796 1.0000
11.500 1.2880 0.03387 0.02713 -0.0518 0.2657 1.0000
11.750 1.2923 0.03563 0.02886 -0.0506 0.2520 1.0000
12.000 1.2972 0.03741 0.03062 -0.0495 0.2382 1.0000
12.250 1.3028 0.03917 0.03237 -0.0486 0.2251 1.0000
12.500 1.3082 0.04100 0.03420 -0.0477 0.2128 1.0000
12.750 1.3137 0.04288 0.03607 -0.0469 0.2010 1.0000
13.000 1.3180 0.04491 0.03808 -0.0461 0.1898 1.0000
13.250 1.3224 0.04697 0.04013 -0.0454 0.1784 1.0000
13.500 1.3281 0.04898 0.04215 -0.0448 0.1675 1.0000
13.750 1.3330 0.05109 0.04428 -0.0443 0.1575 1.0000
14.000 1.3361 0.05344 0.04662 -0.0438 0.1480 1.0000
14.250 1.3417 0.05559 0.04880 -0.0435 0.1385 1.0000
14.500 1.3459 0.05793 0.05116 -0.0431 0.1299 1.0000
14.750 1.3482 0.06051 0.05374 -0.0429 0.1218 1.0000
15.000 1.3535 0.06283 0.05612 -0.0427 0.1138 1.0000
15.250 1.3557 0.06553 0.05884 -0.0426 0.1070 1.0000
15.500 1.3594 0.06811 0.06149 -0.0426 0.0997 1.0000
15.750 1.3615 0.07094 0.06435 -0.0427 0.0935 1.0000
16.000 1.3639 0.07379 0.06724 -0.0429 0.0871 1.0000
16.250 1.3652 0.07682 0.07033 -0.0431 0.0818 1.0000
16.500 1.3669 0.07986 0.07343 -0.0435 0.0764 1.0000
16.750 1.3668 0.08317 0.07678 -0.0439 0.0719 1.0000
17.000 1.3683 0.08633 0.08004 -0.0445 0.0671 1.0000
17.250 1.3663 0.09003 0.08378 -0.0452 0.0633 1.0000
17.500 1.3681 0.09324 0.08710 -0.0459 0.0595 1.0000
17.750 1.3666 0.09697 0.09090 -0.0468 0.0560 1.0000
18.000 1.3643 0.10085 0.09485 -0.0479 0.0530 1.0000
18.250 1.3647 0.10438 0.09849 -0.0489 0.0500 1.0000
18.500 1.3618 0.10846 0.10264 -0.0502 0.0473 1.0000
18.750 1.3584 0.11265 0.10691 -0.0517 0.0450 1.0000
19.000 1.3579 0.11643 0.11081 -0.0531 0.0426 1.0000
19.250 1.3551 0.12061 0.11507 -0.0548 0.0404 1.0000
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Polar data table (+)
Polar graphs
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