EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 50,000 Max Cl/Cd: 14.62 at α=12.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e655-il-50000-n5.txt Download as CSV file: xf-e655-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2446 0.11480 0.10812 -0.0831 0.9499 0.0524
-11.750 -0.2394 0.10922 0.10254 -0.0877 0.9448 0.0531
-11.500 -0.2375 0.10306 0.09638 -0.0926 0.9396 0.0529
-11.000 -0.3032 0.07742 0.07058 -0.1130 0.9269 0.0494
-10.750 -0.3238 0.07128 0.06429 -0.1177 0.9179 0.0492
-10.500 -0.3403 0.06588 0.05866 -0.1218 0.9109 0.0491
-10.250 -0.3614 0.06241 0.05497 -0.1222 0.9011 0.0491
-10.000 -0.3792 0.05899 0.05124 -0.1221 0.8938 0.0492
-9.750 -0.3995 0.05710 0.04911 -0.1189 0.8843 0.0494
-9.500 -0.3994 0.05465 0.04648 -0.1181 0.8788 0.0502
-9.250 -0.4012 0.05306 0.04473 -0.1159 0.8724 0.0513
-9.000 -0.4019 0.05165 0.04317 -0.1137 0.8661 0.0530
-8.750 -0.3978 0.04953 0.04069 -0.1124 0.8617 0.0552
-8.500 -0.4011 0.04783 0.03859 -0.1093 0.8561 0.0572
-8.250 -0.3978 0.04642 0.03698 -0.1067 0.8505 0.0593
-8.000 -0.3824 0.04505 0.03549 -0.1059 0.8467 0.0626
-7.750 -0.3635 0.04320 0.03316 -0.1054 0.8437 0.0678
-7.250 -0.3507 0.04184 0.03171 -0.1000 0.8339 0.0752
-7.000 -0.3312 0.04068 0.03037 -0.0991 0.8306 0.0818
-6.750 -0.3068 0.03961 0.02910 -0.0989 0.8279 0.0909
-6.500 -0.2924 0.03895 0.02849 -0.0972 0.8243 0.0989
-6.250 -0.2903 0.03877 0.02818 -0.0935 0.8190 0.1065
-6.000 -0.2758 0.03824 0.02761 -0.0918 0.8154 0.1184
-5.750 -0.2557 0.03753 0.02690 -0.0910 0.8125 0.1352
-5.500 -0.2334 0.03672 0.02619 -0.0906 0.8101 0.1570
-5.250 -0.2380 0.03678 0.02630 -0.0862 0.8045 0.1708
-5.000 -0.2331 0.03652 0.02611 -0.0832 0.8001 0.1934
-4.750 -0.2181 0.03596 0.02570 -0.0819 0.7968 0.2298
-4.500 -0.1981 0.03523 0.02523 -0.0814 0.7941 0.2825
-4.250 -0.1888 0.03485 0.02514 -0.0793 0.7905 0.3371
-4.000 -0.1916 0.03490 0.02548 -0.0751 0.7852 0.3865
-3.750 -0.1806 0.03477 0.02580 -0.0723 0.7815 0.4683
-3.500 -0.1650 0.03518 0.02663 -0.0687 0.7786 0.5544
-3.250 -0.1437 0.03587 0.02733 -0.0660 0.7762 0.6233
-3.000 -0.1459 0.03672 0.02813 -0.0611 0.7709 0.6599
-2.750 -0.1379 0.03747 0.02874 -0.0575 0.7664 0.6953
-2.500 -0.1224 0.03813 0.02925 -0.0546 0.7629 0.7268
-2.250 -0.1026 0.03868 0.02962 -0.0524 0.7601 0.7559
-2.000 -0.0943 0.03936 0.03019 -0.0486 0.7562 0.7775
-1.750 -0.0925 0.03998 0.03073 -0.0442 0.7508 0.7977
-1.500 -0.0787 0.04041 0.03101 -0.0415 0.7469 0.8193
-1.250 -0.0588 0.04073 0.03118 -0.0395 0.7439 0.8397
-1.000 -0.0359 0.04105 0.03134 -0.0380 0.7412 0.8586
-0.750 -0.0385 0.04159 0.03183 -0.0338 0.7346 0.8759
-0.500 -0.0179 0.04193 0.03204 -0.0327 0.7306 0.8938
-0.250 0.0138 0.04223 0.03218 -0.0334 0.7275 0.9105
0.000 0.0548 0.04254 0.03231 -0.0358 0.7252 0.9245
0.250 0.0672 0.04325 0.03296 -0.0352 0.7182 0.9385
0.500 0.1036 0.04376 0.03333 -0.0379 0.7140 0.9494
0.750 0.1453 0.04415 0.03357 -0.0412 0.7107 0.9586
1.000 0.1959 0.04451 0.03378 -0.0459 0.7083 0.9646
1.250 0.2104 0.04552 0.03476 -0.0467 0.7001 0.9744
1.500 0.2487 0.04600 0.03514 -0.0498 0.6958 0.9816
1.750 0.2926 0.04635 0.03539 -0.0534 0.6927 0.9878
2.000 0.3054 0.04730 0.03634 -0.0537 0.6848 1.0000
2.250 0.3111 0.04747 0.03645 -0.0510 0.6791 1.0000
2.500 0.3308 0.04750 0.03640 -0.0501 0.6757 1.0000
2.750 0.3102 0.04814 0.03703 -0.0446 0.6657 1.0000
3.000 0.3317 0.04839 0.03721 -0.0443 0.6612 1.0000
3.250 0.3395 0.04910 0.03788 -0.0428 0.6539 1.0000
3.500 0.3571 0.04969 0.03843 -0.0426 0.6474 1.0000
3.750 0.3889 0.05000 0.03869 -0.0437 0.6437 1.0000
4.000 0.3937 0.05113 0.03980 -0.0425 0.6340 1.0000
4.250 0.4230 0.05157 0.04021 -0.0434 0.6292 1.0000
4.500 0.4368 0.05256 0.04119 -0.0430 0.6210 1.0000
4.750 0.4613 0.05317 0.04179 -0.0436 0.6147 1.0000
5.000 0.4967 0.05338 0.04198 -0.0449 0.6112 1.0000
5.250 0.5015 0.05478 0.04339 -0.0439 0.6001 1.0000
5.500 0.5358 0.05498 0.04360 -0.0450 0.5962 1.0000
5.750 0.5421 0.05640 0.04504 -0.0443 0.5851 1.0000
6.000 0.5763 0.05653 0.04519 -0.0452 0.5810 1.0000
6.250 0.5830 0.05799 0.04669 -0.0445 0.5698 1.0000
6.500 0.6172 0.05803 0.04676 -0.0454 0.5656 1.0000
6.750 0.6238 0.05955 0.04832 -0.0447 0.5541 1.0000
7.000 0.6588 0.05943 0.04826 -0.0454 0.5501 1.0000
7.250 0.6644 0.06107 0.04995 -0.0447 0.5381 1.0000
7.750 0.7055 0.06248 0.05148 -0.0447 0.5219 1.0000
8.000 0.7162 0.06391 0.05298 -0.0442 0.5111 1.0000
8.250 0.7469 0.06379 0.05295 -0.0445 0.5056 1.0000
8.500 0.7549 0.06545 0.05467 -0.0440 0.4938 1.0000
8.750 0.7887 0.06496 0.05429 -0.0442 0.4892 1.0000
9.000 0.7948 0.06679 0.05620 -0.0437 0.4767 1.0000
9.500 0.8358 0.06792 0.05752 -0.0432 0.4597 1.0000
9.750 0.8444 0.06964 0.05935 -0.0428 0.4479 1.0000
10.000 0.8776 0.06877 0.05860 -0.0426 0.4429 1.0000
10.250 0.8836 0.07077 0.06070 -0.0421 0.4302 1.0000
10.500 0.9203 0.06927 0.05934 -0.0418 0.4262 1.0000
10.750 0.9245 0.07148 0.06166 -0.0413 0.4129 1.0000
11.250 0.9676 0.07175 0.06218 -0.0404 0.3958 1.0000
11.750 1.0143 0.07146 0.06215 -0.0393 0.3786 1.0000
12.000 1.0167 0.07399 0.06479 -0.0389 0.3652 1.0000
12.500 1.0675 0.07303 0.06408 -0.0376 0.3472 1.0000
12.750 1.0690 0.07573 0.06689 -0.0373 0.3338 1.0000
13.000 1.0752 0.07786 0.06913 -0.0370 0.3215 1.0000
13.250 1.1044 0.07678 0.06815 -0.0362 0.3122 1.0000
13.500 1.1237 0.07703 0.06850 -0.0356 0.3010 1.0000
13.750 1.1242 0.07996 0.07155 -0.0355 0.2883 1.0000
14.000 1.1334 0.08172 0.07340 -0.0353 0.2767 1.0000
14.250 1.1575 0.08128 0.07300 -0.0345 0.2659 1.0000
14.500 1.1674 0.08288 0.07468 -0.0342 0.2542 1.0000
14.750 1.1616 0.08689 0.07882 -0.0346 0.2426 1.0000
15.000 1.1687 0.08900 0.08100 -0.0346 0.2318 1.0000
15.250 1.1886 0.08909 0.08107 -0.0339 0.2211 1.0000
15.500 1.1795 0.09377 0.08592 -0.0348 0.2107 1.0000
15.750 1.1781 0.09731 0.08958 -0.0354 0.2009 1.0000
16.000 1.1957 0.09771 0.08994 -0.0349 0.1911 1.0000
16.250 1.1801 0.10371 0.09616 -0.0366 0.1822 1.0000
16.500 1.1836 0.10655 0.09905 -0.0372 0.1735 1.0000
16.750 1.1884 0.10914 0.10170 -0.0377 0.1649 1.0000
17.000 1.1738 0.11537 0.10810 -0.0400 0.1576 1.0000
17.250 1.1937 0.11519 0.10787 -0.0394 0.1493 1.0000
17.500 1.1614 0.12504 0.11800 -0.0437 0.1436 1.0000
17.750 1.1824 0.12452 0.11745 -0.0431 0.1358 1.0000
18.000 1.1443 0.13611 0.12927 -0.0487 0.1310 1.0000
18.250 1.1197 0.14546 0.13875 -0.0535 0.1253 1.0000
18.500 1.1336 0.14629 0.13962 -0.0538 0.1195 1.0000
18.750 1.0633 0.16792 0.16125 -0.0660 0.1132 1.0000
19.000 1.1277 0.15571 0.14917 -0.0588 0.1089 1.0000
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