EPPLER 338 AIRFOIL (e338-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 338 AIRFOIL (e338-il) Reynolds number: 100,000 Max Cl/Cd: 45.93 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e338-il-100000-n5.txt Download as CSV file: xf-e338-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 338 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3437 0.09875 0.09418 -0.0362 1.0000 0.0450
-9.000 -0.3505 0.09465 0.09013 -0.0399 1.0000 0.0450
-8.750 -0.3611 0.09110 0.08662 -0.0418 1.0000 0.0451
-8.250 -0.3527 0.08367 0.07936 -0.0398 1.0000 0.0460
-8.000 -0.3553 0.08073 0.07650 -0.0386 1.0000 0.0465
-7.750 -0.3673 0.07818 0.07403 -0.0370 1.0000 0.0466
-7.500 -0.3607 0.07417 0.07001 -0.0394 0.9763 0.0468
-7.000 -0.3320 0.06055 0.05570 -0.0486 0.8848 0.0308
-6.750 -0.3076 0.05730 0.05231 -0.0508 0.8510 0.0285
-6.500 -0.2965 0.05362 0.04829 -0.0507 0.8213 0.0287
-6.250 -0.2874 0.05027 0.04458 -0.0495 0.7963 0.0290
-5.750 -0.2687 0.04262 0.03591 -0.0446 0.7579 0.0248
-5.500 -0.2547 0.04014 0.03316 -0.0429 0.7403 0.0245
-5.250 -0.2394 0.03779 0.03050 -0.0411 0.7243 0.0241
-5.000 -0.2226 0.03536 0.02769 -0.0393 0.7095 0.0238
-4.750 -0.2041 0.03302 0.02492 -0.0375 0.6957 0.0235
-4.500 -0.1836 0.03088 0.02233 -0.0358 0.6827 0.0233
-4.250 -0.1613 0.02887 0.01988 -0.0343 0.6706 0.0232
-4.000 -0.1373 0.02705 0.01765 -0.0331 0.6580 0.0234
-3.750 -0.1114 0.02542 0.01565 -0.0321 0.6462 0.0237
-3.500 -0.0842 0.02400 0.01387 -0.0314 0.6355 0.0242
-3.250 -0.0572 0.02285 0.01251 -0.0309 0.6244 0.0256
-3.000 -0.0312 0.02208 0.01166 -0.0304 0.6137 0.0282
-2.750 -0.0044 0.02119 0.01053 -0.0297 0.6042 0.0305
-2.500 0.0199 0.02036 0.00971 -0.0289 0.5941 0.0324
-2.250 0.0436 0.01975 0.00897 -0.0278 0.5855 0.0363
-2.000 0.0664 0.01920 0.00839 -0.0267 0.5765 0.0430
-1.750 0.0896 0.01870 0.00780 -0.0256 0.5684 0.0524
-1.500 0.1690 0.01607 0.00826 -0.0334 0.5576 0.8174
-1.250 0.2031 0.01738 0.00927 -0.0320 0.5490 0.9233
-1.000 0.3412 0.01758 0.00880 -0.0524 0.5354 0.9835
-0.750 0.3752 0.01744 0.00844 -0.0539 0.5274 0.9881
-0.500 0.4071 0.01735 0.00814 -0.0550 0.5205 0.9919
-0.250 0.4382 0.01728 0.00792 -0.0560 0.5131 0.9954
0.000 0.4696 0.01722 0.00764 -0.0570 0.5073 0.9985
0.250 0.4963 0.01723 0.00758 -0.0572 0.5003 1.0000
0.500 0.5188 0.01731 0.00753 -0.0564 0.4945 1.0000
0.750 0.5414 0.01742 0.00752 -0.0556 0.4893 1.0000
1.000 0.5640 0.01753 0.00758 -0.0549 0.4834 1.0000
1.250 0.5867 0.01765 0.00759 -0.0541 0.4783 1.0000
1.500 0.6094 0.01778 0.00764 -0.0533 0.4736 1.0000
1.750 0.6318 0.01793 0.00777 -0.0525 0.4679 1.0000
2.000 0.6544 0.01808 0.00785 -0.0517 0.4632 1.0000
2.250 0.6773 0.01824 0.00791 -0.0510 0.4592 1.0000
2.500 0.6994 0.01843 0.00814 -0.0501 0.4538 1.0000
2.750 0.7217 0.01861 0.00830 -0.0493 0.4489 1.0000
3.000 0.7443 0.01879 0.00841 -0.0485 0.4449 1.0000
3.250 0.7665 0.01901 0.00865 -0.0477 0.4406 1.0000
3.500 0.7882 0.01924 0.00892 -0.0468 0.4358 1.0000
3.750 0.8103 0.01945 0.00912 -0.0459 0.4314 1.0000
4.000 0.8329 0.01966 0.00927 -0.0451 0.4280 1.0000
4.250 0.8536 0.01996 0.00966 -0.0441 0.4232 1.0000
4.500 0.8747 0.02023 0.00998 -0.0431 0.4186 1.0000
4.750 0.8963 0.02047 0.01023 -0.0422 0.4147 1.0000
5.000 0.9181 0.02074 0.01048 -0.0412 0.4112 1.0000
5.250 0.9373 0.02111 0.01098 -0.0400 0.4063 1.0000
5.500 0.9575 0.02141 0.01135 -0.0389 0.4019 1.0000
5.750 0.9788 0.02168 0.01162 -0.0378 0.3982 1.0000
6.000 0.9987 0.02202 0.01202 -0.0367 0.3943 1.0000
6.250 1.0164 0.02243 0.01258 -0.0352 0.3895 1.0000
6.500 1.0358 0.02275 0.01297 -0.0339 0.3851 1.0000
6.750 1.0569 0.02301 0.01322 -0.0328 0.3816 1.0000
7.000 1.0729 0.02348 0.01385 -0.0311 0.3767 1.0000
7.250 1.0895 0.02388 0.01440 -0.0294 0.3719 1.0000
7.500 1.1088 0.02416 0.01471 -0.0281 0.3677 1.0000
7.750 1.1261 0.02453 0.01515 -0.0265 0.3635 1.0000
8.000 1.1389 0.02505 0.01586 -0.0243 0.3581 1.0000
8.250 1.1556 0.02537 0.01626 -0.0226 0.3535 1.0000
8.500 1.1745 0.02563 0.01653 -0.0212 0.3496 1.0000
8.750 1.1823 0.02625 0.01740 -0.0182 0.3438 1.0000
9.000 1.1961 0.02658 0.01781 -0.0160 0.3387 1.0000
9.250 1.2123 0.02681 0.01808 -0.0142 0.3340 1.0000
9.500 1.2159 0.02743 0.01892 -0.0106 0.3277 1.0000
9.750 1.2280 0.02770 0.01927 -0.0081 0.3225 1.0000
10.000 1.2365 0.02812 0.01978 -0.0052 0.3174 1.0000
10.250 1.2387 0.02872 0.02057 -0.0015 0.3116 1.0000
10.500 1.2499 0.02895 0.02084 0.0010 0.3065 1.0000
10.750 1.2492 0.02963 0.02168 0.0050 0.3007 1.0000
11.000 1.2511 0.03016 0.02232 0.0086 0.2945 1.0000
11.250 1.2543 0.03060 0.02281 0.0119 0.2887 1.0000
11.500 1.2485 0.03159 0.02395 0.0158 0.2821 1.0000
11.750 1.2558 0.03209 0.02449 0.0180 0.2758 1.0000
12.000 1.2465 0.03374 0.02633 0.0209 0.2686 1.0000
12.250 1.2516 0.03461 0.02722 0.0226 0.2618 1.0000
12.500 1.2394 0.03703 0.02984 0.0243 0.2543 1.0000
12.750 1.2407 0.03856 0.03140 0.0253 0.2472 1.0000
13.000 1.2268 0.04176 0.03476 0.0259 0.2397 1.0000
13.250 1.2244 0.04401 0.03706 0.0263 0.2324 1.0000
13.500 1.2089 0.04791 0.04109 0.0261 0.2248 1.0000
13.750 1.2017 0.05102 0.04426 0.0259 0.2175 1.0000
14.000 1.1895 0.05490 0.04821 0.0253 0.2098 1.0000
14.250 1.1769 0.05899 0.05239 0.0246 0.2024 1.0000
14.500 1.1720 0.06211 0.05555 0.0241 0.1948 1.0000
14.750 1.1568 0.06690 0.06044 0.0229 0.1880 1.0000
15.000 1.1585 0.06929 0.06283 0.0225 0.1806 1.0000
15.250 1.1405 0.07480 0.06848 0.0208 0.1735 1.0000
15.500 1.1461 0.07675 0.07040 0.0205 0.1665 1.0000
15.750 1.1285 0.08251 0.07630 0.0185 0.1594 1.0000
16.000 1.1320 0.08488 0.07867 0.0179 0.1525 1.0000
16.250 1.1178 0.09034 0.08425 0.0159 0.1454 1.0000
16.500 1.1181 0.09337 0.08729 0.0149 0.1386 1.0000
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Polar data table (+)
Polar graphs
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