EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 200,000 Max Cl/Cd: 92 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e395-il-200000-n5.txt Download as CSV file: xf-e395-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 395 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3491 0.08168 0.07813 -0.0768 0.9831 0.0098
-10.250 -0.4000 0.05914 0.05540 -0.0955 0.9610 0.0091
-10.000 -0.4201 0.04895 0.04502 -0.1062 0.9469 0.0086
-9.750 -0.4239 0.03817 0.03388 -0.1226 0.9327 0.0085
-9.500 -0.4040 0.03240 0.02765 -0.1338 0.9228 0.0091
-9.250 -0.3763 0.02886 0.02365 -0.1401 0.9175 0.0098
-9.000 -0.3521 0.02671 0.02128 -0.1430 0.9101 0.0105
-8.750 -0.3223 0.02500 0.01936 -0.1461 0.9048 0.0114
-8.500 -0.2909 0.02317 0.01723 -0.1490 0.9001 0.0124
-8.250 -0.2649 0.02164 0.01547 -0.1504 0.8926 0.0134
-8.000 -0.2324 0.02033 0.01397 -0.1528 0.8880 0.0149
-7.750 -0.2040 0.01916 0.01261 -0.1541 0.8816 0.0172
-7.500 -0.1739 0.01828 0.01158 -0.1554 0.8756 0.0211
-7.250 -0.1411 0.01744 0.01062 -0.1571 0.8711 0.0266
-7.000 -0.1146 0.01683 0.00990 -0.1575 0.8639 0.0325
-6.750 -0.0837 0.01624 0.00919 -0.1586 0.8586 0.0398
-6.500 -0.0545 0.01575 0.00860 -0.1593 0.8529 0.0476
-6.000 0.0048 0.01478 0.00749 -0.1608 0.8419 0.0647
-5.750 0.0323 0.01441 0.00705 -0.1610 0.8357 0.0742
-5.500 0.0613 0.01408 0.00663 -0.1615 0.8301 0.0849
-5.250 0.0918 0.01376 0.00622 -0.1622 0.8255 0.0973
-5.000 0.1189 0.01350 0.00593 -0.1622 0.8193 0.1100
-4.750 0.1480 0.01325 0.00562 -0.1627 0.8141 0.1245
-4.500 0.1776 0.01302 0.00535 -0.1632 0.8094 0.1405
-4.250 0.2050 0.01284 0.00516 -0.1633 0.8036 0.1566
-4.000 0.2341 0.01266 0.00495 -0.1637 0.7986 0.1742
-3.750 0.2633 0.01251 0.00477 -0.1640 0.7941 0.1923
-3.500 0.2908 0.01239 0.00465 -0.1641 0.7884 0.2107
-3.250 0.3197 0.01229 0.00451 -0.1644 0.7836 0.2299
-3.000 0.3489 0.01219 0.00439 -0.1647 0.7792 0.2487
-2.750 0.3762 0.01211 0.00433 -0.1647 0.7736 0.2676
-2.500 0.4048 0.01204 0.00424 -0.1649 0.7688 0.2870
-2.250 0.4342 0.01198 0.00415 -0.1653 0.7647 0.3071
-2.000 0.4612 0.01194 0.00414 -0.1652 0.7591 0.3263
-1.750 0.4895 0.01189 0.00411 -0.1653 0.7542 0.3466
-1.500 0.5189 0.01185 0.00405 -0.1657 0.7503 0.3685
-1.250 0.5458 0.01184 0.00409 -0.1655 0.7447 0.3897
-1.000 0.5737 0.01181 0.00410 -0.1656 0.7397 0.4125
-0.750 0.6028 0.01179 0.00409 -0.1659 0.7356 0.4363
-0.500 0.6296 0.01179 0.00416 -0.1657 0.7301 0.4608
-0.250 0.6572 0.01178 0.00421 -0.1657 0.7250 0.4865
0.000 0.6859 0.01177 0.00424 -0.1658 0.7207 0.5141
0.250 0.7125 0.01179 0.00434 -0.1657 0.7153 0.5425
0.500 0.7395 0.01179 0.00443 -0.1655 0.7099 0.5724
0.750 0.7675 0.01179 0.00448 -0.1654 0.7055 0.6044
1.000 0.7932 0.01181 0.00463 -0.1650 0.6997 0.6369
1.250 0.8193 0.01182 0.00474 -0.1646 0.6943 0.6712
1.500 0.8463 0.01183 0.00480 -0.1643 0.6898 0.7082
1.750 0.8698 0.01185 0.00497 -0.1634 0.6835 0.7467
2.000 0.8935 0.01184 0.00507 -0.1623 0.6779 0.7890
2.250 0.9158 0.01182 0.00514 -0.1609 0.6727 0.8385
2.500 0.9339 0.01174 0.00520 -0.1586 0.6662 0.9130
2.750 0.9632 0.01176 0.00521 -0.1588 0.6605 1.0000
3.000 0.9897 0.01191 0.00537 -0.1587 0.6535 1.0000
3.250 1.0171 0.01204 0.00547 -0.1587 0.6467 1.0000
3.500 1.0436 0.01218 0.00564 -0.1585 0.6394 1.0000
3.750 1.0703 0.01232 0.00577 -0.1583 0.6318 1.0000
4.000 1.0960 0.01247 0.00594 -0.1580 0.6234 1.0000
4.250 1.1224 0.01262 0.00608 -0.1577 0.6151 1.0000
4.500 1.1470 0.01278 0.00629 -0.1571 0.6052 1.0000
4.750 1.1722 0.01295 0.00646 -0.1566 0.5956 1.0000
5.000 1.1969 0.01313 0.00665 -0.1560 0.5851 1.0000
5.250 1.2205 0.01333 0.00688 -0.1553 0.5734 1.0000
5.500 1.2439 0.01354 0.00712 -0.1545 0.5614 1.0000
5.750 1.2669 0.01377 0.00736 -0.1536 0.5485 1.0000
6.000 1.2889 0.01403 0.00764 -0.1525 0.5341 1.0000
6.250 1.3099 0.01431 0.00793 -0.1512 0.5179 1.0000
6.500 1.3298 0.01464 0.00824 -0.1498 0.4999 1.0000
6.750 1.3480 0.01503 0.00859 -0.1480 0.4802 1.0000
7.000 1.3647 0.01546 0.00900 -0.1461 0.4580 1.0000
7.250 1.3787 0.01598 0.00945 -0.1436 0.4340 1.0000
7.500 1.3893 0.01656 0.00995 -0.1406 0.4075 1.0000
7.750 1.3977 0.01725 0.01055 -0.1373 0.3799 1.0000
8.000 1.4040 0.01807 0.01127 -0.1338 0.3507 1.0000
8.250 1.4085 0.01904 0.01212 -0.1301 0.3204 1.0000
8.500 1.4120 0.02014 0.01309 -0.1265 0.2904 1.0000
8.750 1.4147 0.02137 0.01420 -0.1231 0.2611 1.0000
9.000 1.4172 0.02271 0.01542 -0.1198 0.2330 1.0000
9.250 1.4197 0.02416 0.01675 -0.1167 0.2066 1.0000
9.500 1.4222 0.02570 0.01819 -0.1139 0.1823 1.0000
9.750 1.4261 0.02725 0.01967 -0.1114 0.1595 1.0000
10.000 1.4294 0.02893 0.02129 -0.1090 0.1395 1.0000
10.250 1.4338 0.03061 0.02292 -0.1069 0.1209 1.0000
10.500 1.4376 0.03240 0.02467 -0.1049 0.1039 1.0000
10.750 1.4410 0.03431 0.02652 -0.1030 0.0888 1.0000
11.000 1.4443 0.03629 0.02848 -0.1012 0.0753 1.0000
11.250 1.4477 0.03833 0.03050 -0.0996 0.0636 1.0000
11.500 1.4512 0.04042 0.03259 -0.0981 0.0535 1.0000
11.750 1.4549 0.04257 0.03478 -0.0967 0.0452 1.0000
12.000 1.4584 0.04479 0.03704 -0.0954 0.0386 1.0000
12.250 1.4609 0.04719 0.03948 -0.0942 0.0333 1.0000
12.500 1.4637 0.04964 0.04198 -0.0931 0.0287 1.0000
12.750 1.4663 0.05217 0.04460 -0.0922 0.0252 1.0000
13.000 1.4676 0.05492 0.04741 -0.0913 0.0223 1.0000
13.250 1.4695 0.05769 0.05029 -0.0906 0.0198 1.0000
13.500 1.4704 0.06066 0.05335 -0.0900 0.0178 1.0000
13.750 1.4700 0.06387 0.05667 -0.0896 0.0162 1.0000
14.000 1.4710 0.06699 0.05994 -0.0893 0.0146 1.0000
14.250 1.4696 0.07051 0.06354 -0.0892 0.0134 1.0000
14.500 1.4688 0.07406 0.06723 -0.0892 0.0123 1.0000
14.750 1.4676 0.07773 0.07105 -0.0893 0.0114 1.0000
15.000 1.4652 0.08166 0.07511 -0.0897 0.0108 1.0000
15.250 1.4605 0.08604 0.07961 -0.0903 0.0102 1.0000
15.500 1.4566 0.09043 0.08415 -0.0910 0.0097 1.0000
15.750 1.4536 0.09476 0.08864 -0.0919 0.0092 1.0000
16.000 1.4504 0.09917 0.09320 -0.0929 0.0087 1.0000
16.250 1.4471 0.10369 0.09785 -0.0942 0.0082 1.0000
16.500 1.4428 0.10846 0.10275 -0.0958 0.0078 1.0000
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Polar data table (+)
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