EPPLER 338 AIRFOIL (e338-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 338 AIRFOIL (e338-il) Reynolds number: 100,000 Max Cl/Cd: 33.76 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e338-il-100000.txt Download as CSV file: xf-e338-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3286 0.09557 0.09118 -0.0322 1.0000 0.0780
-8.500 -0.3464 0.09224 0.08795 -0.0371 1.0000 0.0789
-8.250 -0.3700 0.09006 0.08583 -0.0379 1.0000 0.0793
-8.000 -0.3958 0.08860 0.08438 -0.0366 1.0000 0.0796
-7.750 -0.4139 0.08720 0.08295 -0.0346 1.0000 0.0798
-7.500 -0.3723 0.07937 0.07542 -0.0339 1.0000 0.0828
-7.250 -0.3749 0.07697 0.07314 -0.0318 1.0000 0.0847
-7.000 -0.4003 0.07628 0.07264 -0.0271 1.0000 0.0853
-6.750 -0.3743 0.07155 0.06778 -0.0350 0.9800 0.0912
-6.500 -0.3523 0.06584 0.06184 -0.0418 0.9554 0.0973
-6.250 -0.3294 0.06400 0.05939 -0.0470 0.9323 0.1105
-6.000 -0.2890 0.05688 0.05265 -0.0505 0.9180 0.1177
-5.750 -0.2677 0.05323 0.04867 -0.0530 0.8933 0.1299
-5.500 -0.2486 0.05033 0.04546 -0.0537 0.8703 0.1453
-5.250 -0.2342 0.04830 0.04315 -0.0528 0.8460 0.1609
-5.000 -0.2193 0.04568 0.04041 -0.0515 0.8249 0.1779
-4.750 -0.2042 0.04307 0.03774 -0.0500 0.8059 0.1965
-4.500 -0.1899 0.04108 0.03566 -0.0480 0.7883 0.2193
-4.250 -0.1788 0.03909 0.03361 -0.0455 0.7719 0.2506
-4.000 -0.1671 0.03713 0.03158 -0.0429 0.7566 0.2825
-3.750 -0.1044 0.03207 0.02405 -0.0418 0.7458 0.0778
-3.500 -0.0780 0.02968 0.02105 -0.0397 0.7332 0.0652
-3.250 -0.0520 0.02750 0.01856 -0.0386 0.7211 0.0620
-3.000 -0.0256 0.02597 0.01672 -0.0374 0.7078 0.0610
-2.750 0.0016 0.02487 0.01534 -0.0365 0.6956 0.0636
-2.500 0.0308 0.02378 0.01398 -0.0358 0.6849 0.0653
-2.250 0.0609 0.02239 0.01248 -0.0354 0.6737 0.0680
-2.000 0.3183 0.01819 0.01084 -0.0705 0.6519 1.0000
-1.750 0.3394 0.01823 0.01064 -0.0696 0.6416 1.0000
-1.500 0.3607 0.01831 0.01050 -0.0687 0.6318 1.0000
-1.250 0.3823 0.01838 0.01032 -0.0677 0.6232 1.0000
-1.000 0.4039 0.01852 0.01033 -0.0670 0.6141 1.0000
-0.750 0.4260 0.01863 0.01023 -0.0661 0.6066 1.0000
-0.500 0.4477 0.01881 0.01031 -0.0653 0.5981 1.0000
-0.250 0.4700 0.01894 0.01027 -0.0644 0.5910 1.0000
0.000 0.4919 0.01917 0.01041 -0.0637 0.5836 1.0000
0.250 0.5142 0.01937 0.01050 -0.0629 0.5767 1.0000
0.500 0.5368 0.01959 0.01058 -0.0621 0.5710 1.0000
0.750 0.5583 0.01987 0.01085 -0.0613 0.5633 1.0000
1.000 0.5812 0.02007 0.01091 -0.0605 0.5578 1.0000
1.250 0.6027 0.02042 0.01126 -0.0598 0.5515 1.0000
1.500 0.6247 0.02072 0.01153 -0.0590 0.5453 1.0000
1.750 0.6480 0.02094 0.01161 -0.0582 0.5405 1.0000
2.000 0.6683 0.02141 0.01215 -0.0573 0.5340 1.0000
2.250 0.6902 0.02175 0.01246 -0.0565 0.5285 1.0000
2.500 0.7137 0.02201 0.01262 -0.0558 0.5242 1.0000
2.750 0.7326 0.02260 0.01333 -0.0547 0.5179 1.0000
3.000 0.7539 0.02298 0.01370 -0.0538 0.5124 1.0000
3.250 0.7772 0.02329 0.01392 -0.0530 0.5084 1.0000
3.500 0.7947 0.02401 0.01478 -0.0518 0.5026 1.0000
3.750 0.8148 0.02450 0.01532 -0.0508 0.4971 1.0000
4.000 0.8376 0.02481 0.01557 -0.0499 0.4930 1.0000
4.250 0.8545 0.02561 0.01647 -0.0486 0.4878 1.0000
4.500 0.8717 0.02632 0.01728 -0.0472 0.4822 1.0000
4.750 0.8941 0.02662 0.01757 -0.0463 0.4779 1.0000
5.000 0.9125 0.02731 0.01830 -0.0451 0.4734 1.0000
5.250 0.9244 0.02836 0.01954 -0.0431 0.4671 1.0000
5.500 0.9462 0.02869 0.01985 -0.0421 0.4627 1.0000
5.750 0.9701 0.02900 0.02013 -0.0414 0.4590 1.0000
6.000 0.9720 0.03066 0.02208 -0.0384 0.4520 1.0000
6.250 0.9924 0.03102 0.02246 -0.0372 0.4473 1.0000
6.500 1.0202 0.03102 0.02237 -0.0368 0.4437 1.0000
6.750 1.0131 0.03317 0.02486 -0.0327 0.4364 1.0000
7.000 1.0329 0.03350 0.02523 -0.0314 0.4316 1.0000
7.250 1.0648 0.03320 0.02484 -0.0314 0.4280 1.0000
7.500 1.0446 0.03597 0.02795 -0.0259 0.4203 1.0000
7.750 1.0678 0.03601 0.02802 -0.0248 0.4155 1.0000
8.000 1.1065 0.03534 0.02725 -0.0255 0.4120 1.0000
8.250 1.0614 0.03923 0.03152 -0.0173 0.4037 1.0000
8.500 1.0971 0.03845 0.03073 -0.0174 0.3992 1.0000
8.750 1.1091 0.03913 0.03149 -0.0152 0.3942 1.0000
9.000 1.0524 0.04329 0.03584 -0.0060 0.3866 1.0000
9.250 1.1361 0.03983 0.03234 -0.0107 0.3825 1.0000
9.500 0.8665 0.06040 0.05288 0.0075 0.3667 1.0000
9.750 0.9824 0.05075 0.04342 0.0088 0.3680 1.0000
10.000 1.1912 0.04015 0.03284 -0.0058 0.3653 1.0000
10.250 0.9102 0.06251 0.05517 0.0109 0.3497 1.0000
10.500 1.0682 0.04882 0.04174 0.0115 0.3521 1.0000
11.000 0.9847 0.06051 0.05344 0.0150 0.3350 1.0000
11.250 1.2052 0.04421 0.03739 0.0096 0.3341 1.0000
11.750 1.2505 0.04297 0.03629 0.0122 0.3192 1.0000
12.250 1.2016 0.04777 0.04128 0.0204 0.3065 1.0000
12.750 1.2803 0.04391 0.03754 0.0213 0.2894 1.0000
13.250 1.2717 0.04671 0.04054 0.0251 0.2747 1.0000
13.750 1.2478 0.05195 0.04597 0.0270 0.2603 1.0000
14.000 1.3190 0.04670 0.04067 0.0280 0.2479 1.0000
14.250 0.7879 0.13079 0.12413 -0.0024 0.2295 1.0000
14.500 0.8518 0.12247 0.11601 0.0025 0.2214 1.0000
14.750 0.8028 0.13499 0.12848 -0.0033 0.2137 1.0000
15.000 0.8557 0.12879 0.12246 0.0006 0.2079 1.0000
15.250 1.2427 0.06445 0.05886 0.0280 0.2093 1.0000
15.500 1.1810 0.07549 0.06998 0.0245 0.2048 1.0000
15.750 1.1776 0.07843 0.07298 0.0238 0.1957 1.0000
16.000 1.2521 0.06991 0.06433 0.0280 0.1779 1.0000
16.250 1.1893 0.08172 0.07636 0.0236 0.1756 1.0000
16.500 1.2135 0.08052 0.07509 0.0247 0.1623 1.0000
16.750 1.2251 0.08136 0.07584 0.0250 0.1507 1.0000
17.000 1.1859 0.09044 0.08511 0.0214 0.1470 1.0000
17.250 1.1303 0.10303 0.09785 0.0159 0.1446 1.0000
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Polar data table (+)
Polar graphs
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