EPPLER 625 AIRFOIL (e625-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 625 AIRFOIL (e625-il) Reynolds number: 100,000 Max Cl/Cd: 39.17 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e625-il-100000.txt Download as CSV file: xf-e625-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 625 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4171 0.10047 0.09581 -0.0200 1.0000 0.1102
-9.250 -0.4555 0.09651 0.09192 -0.0274 1.0000 0.1111
-9.000 -0.4901 0.09441 0.08982 -0.0273 1.0000 0.1114
-8.750 -0.4104 0.08860 0.08411 -0.0221 1.0000 0.1165
-8.500 -0.4129 0.08501 0.08057 -0.0236 1.0000 0.1198
-8.250 -0.4305 0.08131 0.07692 -0.0256 1.0000 0.1229
-8.000 -0.4739 0.07939 0.07498 -0.0245 1.0000 0.1257
-7.750 -0.5205 0.07971 0.07501 -0.0208 1.0000 0.1269
-7.500 -0.4755 0.07190 0.06759 -0.0221 1.0000 0.1303
-7.250 -0.4698 0.06922 0.06497 -0.0203 1.0000 0.1341
-7.000 -0.4815 0.06719 0.06293 -0.0177 1.0000 0.1388
-6.750 -0.5385 0.06974 0.06520 -0.0089 1.0000 0.1425
-6.500 -0.5670 0.06898 0.06443 -0.0027 1.0000 0.1431
-6.250 -0.5260 0.06203 0.05782 -0.0064 0.9943 0.1474
-6.000 -0.4999 0.05815 0.05364 -0.0107 0.9793 0.1613
-5.750 -0.4706 0.05477 0.05003 -0.0139 0.9658 0.1770
-5.500 -0.4355 0.05079 0.04601 -0.0173 0.9557 0.1945
-5.250 -0.4021 0.04729 0.04254 -0.0196 0.9437 0.2151
-5.000 -0.3694 0.03639 0.02918 -0.0172 0.9299 0.0818
-4.750 -0.3325 0.03250 0.02499 -0.0187 0.9185 0.0768
-4.500 -0.2932 0.02917 0.02080 -0.0193 0.9075 0.0719
-4.250 -0.2577 0.02728 0.01855 -0.0197 0.8927 0.0714
-4.000 -0.2235 0.02546 0.01662 -0.0204 0.8774 0.0735
-3.750 -0.1920 0.02430 0.01536 -0.0203 0.8615 0.0777
-3.500 -0.1602 0.02313 0.01399 -0.0201 0.8458 0.0810
-3.250 -0.1283 0.02181 0.01262 -0.0199 0.8301 0.0850
-3.000 -0.1012 0.02091 0.01174 -0.0191 0.8143 0.0932
-2.750 -0.0772 0.02006 0.01096 -0.0177 0.7990 0.1083
-2.500 0.1843 0.01943 0.01302 -0.0505 0.7810 0.9787
-2.250 0.2522 0.01844 0.01164 -0.0582 0.7607 1.0000
-2.000 0.2714 0.01838 0.01135 -0.0566 0.7431 1.0000
-1.750 0.2906 0.01834 0.01111 -0.0551 0.7260 1.0000
-1.500 0.3103 0.01830 0.01088 -0.0537 0.7100 1.0000
-1.250 0.3302 0.01828 0.01068 -0.0523 0.6944 1.0000
-1.000 0.3505 0.01827 0.01051 -0.0510 0.6788 1.0000
-0.750 0.3709 0.01827 0.01037 -0.0497 0.6636 1.0000
-0.500 0.3916 0.01829 0.01025 -0.0485 0.6488 1.0000
-0.250 0.4125 0.01833 0.01016 -0.0473 0.6346 1.0000
0.000 0.4335 0.01838 0.01007 -0.0461 0.6208 1.0000
0.250 0.4547 0.01843 0.00998 -0.0449 0.6077 1.0000
0.500 0.4761 0.01849 0.00987 -0.0437 0.5951 1.0000
0.750 0.4974 0.01858 0.00989 -0.0426 0.5813 1.0000
1.000 0.5188 0.01869 0.00992 -0.0415 0.5681 1.0000
1.250 0.5404 0.01881 0.00995 -0.0404 0.5557 1.0000
1.500 0.5623 0.01893 0.00991 -0.0393 0.5448 1.0000
1.750 0.5838 0.01907 0.01000 -0.0382 0.5322 1.0000
2.000 0.6053 0.01925 0.01014 -0.0372 0.5200 1.0000
2.250 0.6272 0.01944 0.01023 -0.0361 0.5093 1.0000
2.500 0.6492 0.01960 0.01030 -0.0351 0.4988 1.0000
2.750 0.6705 0.01986 0.01056 -0.0341 0.4874 1.0000
3.000 0.6924 0.02008 0.01070 -0.0330 0.4776 1.0000
3.250 0.7141 0.02030 0.01087 -0.0320 0.4675 1.0000
3.500 0.7353 0.02061 0.01120 -0.0310 0.4574 1.0000
3.750 0.7580 0.02083 0.01127 -0.0300 0.4493 1.0000
4.000 0.7783 0.02118 0.01172 -0.0289 0.4388 1.0000
4.250 0.8004 0.02147 0.01191 -0.0279 0.4307 1.0000
4.500 0.8210 0.02181 0.01232 -0.0268 0.4213 1.0000
4.750 0.8423 0.02217 0.01265 -0.0258 0.4132 1.0000
5.000 0.8631 0.02251 0.01301 -0.0247 0.4046 1.0000
5.250 0.8838 0.02294 0.01346 -0.0236 0.3968 1.0000
5.500 0.9042 0.02331 0.01384 -0.0224 0.3887 1.0000
5.750 0.9245 0.02378 0.01433 -0.0213 0.3812 1.0000
6.000 0.9440 0.02423 0.01482 -0.0200 0.3734 1.0000
6.250 0.9647 0.02471 0.01529 -0.0189 0.3666 1.0000
6.500 0.9825 0.02526 0.01596 -0.0175 0.3587 1.0000
6.750 1.0048 0.02565 0.01624 -0.0165 0.3525 1.0000
7.000 1.0194 0.02639 0.01721 -0.0147 0.3445 1.0000
7.250 1.0419 0.02674 0.01746 -0.0138 0.3386 1.0000
7.500 1.0551 0.02760 0.01854 -0.0118 0.3311 1.0000
7.750 1.0750 0.02803 0.01895 -0.0106 0.3247 1.0000
8.000 1.0909 0.02884 0.01987 -0.0089 0.3185 1.0000
8.250 1.1055 0.02955 0.02070 -0.0070 0.3116 1.0000
8.500 1.1297 0.02994 0.02093 -0.0064 0.3062 1.0000
8.750 1.1349 0.03110 0.02243 -0.0034 0.2992 1.0000
9.000 1.1541 0.03159 0.02291 -0.0020 0.2935 1.0000
9.250 1.1667 0.03257 0.02400 0.0000 0.2879 1.0000
9.500 1.1749 0.03356 0.02518 0.0026 0.2817 1.0000
9.750 1.2003 0.03381 0.02529 0.0032 0.2763 1.0000
10.000 1.1986 0.03537 0.02717 0.0069 0.2709 1.0000
10.250 1.2079 0.03630 0.02822 0.0093 0.2654 1.0000
10.500 1.2384 0.03652 0.02824 0.0092 0.2603 1.0000
10.750 1.2224 0.03848 0.03061 0.0145 0.2554 1.0000
11.000 1.2284 0.03951 0.03175 0.0173 0.2503 1.0000
11.250 1.2646 0.03959 0.03164 0.0164 0.2452 1.0000
11.500 1.2362 0.04203 0.03448 0.0229 0.2415 1.0000
11.750 1.2240 0.04385 0.03649 0.0272 0.2373 1.0000
12.000 1.2622 0.04348 0.03600 0.0265 0.2317 1.0000
12.250 1.2468 0.04564 0.03833 0.0309 0.2285 1.0000
12.500 1.1947 0.04894 0.04185 0.0387 0.2266 1.0000
13.000 1.2629 0.04897 0.04183 0.0380 0.2157 1.0000
13.250 1.1460 0.05698 0.05015 0.0456 0.2170 1.0000
13.500 0.6720 0.14385 0.13687 0.0079 0.2603 1.0000
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Polar data table (+)
Polar graphs
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