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