XFOIL Version 6.96 Calculated polar for: EPPLER 818 HYDROFOIL AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4687 0.09941 0.09245 -0.0444 1.0000 0.0196 -9.250 -0.4743 0.09552 0.08864 -0.0449 1.0000 0.0194 -9.000 -0.4813 0.09149 0.08471 -0.0454 1.0000 0.0191 -8.750 -0.4896 0.08751 0.08081 -0.0458 1.0000 0.0187 -8.500 -0.5007 0.08336 0.07675 -0.0463 1.0000 0.0185 -8.250 -0.5146 0.07938 0.07285 -0.0467 1.0000 0.0182 -8.000 -0.5315 0.07581 0.06933 -0.0467 1.0000 0.0180 -7.750 -0.5508 0.07222 0.06579 -0.0470 1.0000 0.0179 -7.500 -0.5655 0.06806 0.06160 -0.0489 1.0000 0.0177 -7.250 -0.5764 0.06390 0.05733 -0.0502 1.0000 0.0175 -7.000 -0.5819 0.05972 0.05295 -0.0514 1.0000 0.0173 -6.750 -0.5816 0.05545 0.04838 -0.0527 1.0000 0.0171 -6.500 -0.5751 0.05127 0.04382 -0.0540 1.0000 0.0169 -6.250 -0.5630 0.04717 0.03926 -0.0551 1.0000 0.0168 -6.000 -0.5464 0.04361 0.03520 -0.0559 1.0000 0.0168 -5.750 -0.5263 0.04038 0.03145 -0.0563 1.0000 0.0177 -5.500 -0.5044 0.03775 0.02833 -0.0564 1.0000 0.0187 -5.250 -0.4814 0.03573 0.02582 -0.0560 1.0000 0.0206 -5.000 -0.4592 0.03338 0.02319 -0.0556 1.0000 0.0230 -4.750 -0.4370 0.03152 0.02113 -0.0553 1.0000 0.0260 -4.500 -0.4135 0.02996 0.01931 -0.0548 1.0000 0.0286 -4.250 -0.3878 0.02843 0.01727 -0.0548 1.0000 0.0311 -4.000 -0.3592 0.02678 0.01530 -0.0558 1.0000 0.0357 -3.750 -0.3268 0.02438 0.01308 -0.0582 1.0000 0.0755 -3.500 -0.3010 0.02326 0.01423 -0.0589 1.0000 0.4825 -3.250 -0.2765 0.02307 0.01364 -0.0581 1.0000 0.5013 -3.000 -0.2519 0.02291 0.01316 -0.0577 1.0000 0.5210 -2.750 -0.2282 0.02279 0.01281 -0.0570 1.0000 0.5397 -2.500 -0.2039 0.02270 0.01248 -0.0566 1.0000 0.5599 -2.250 -0.1810 0.02264 0.01227 -0.0558 1.0000 0.5787 -2.000 -0.1574 0.02260 0.01207 -0.0553 1.0000 0.5995 -1.750 -0.1351 0.02259 0.01180 -0.0545 1.0000 0.6193 -1.500 -0.1124 0.02260 0.01171 -0.0538 1.0000 0.6403 -1.250 -0.0905 0.02262 0.01168 -0.0529 1.0000 0.6612 -1.000 -0.0691 0.02266 0.01168 -0.0520 1.0000 0.6826 -0.750 -0.0477 0.02272 0.01171 -0.0511 1.0000 0.7055 -0.500 -0.0274 0.02277 0.01177 -0.0499 1.0000 0.7285 -0.250 -0.0080 0.02283 0.01179 -0.0486 1.0000 0.7527 0.000 0.0115 0.02289 0.01188 -0.0473 0.9995 0.7793 0.250 0.0378 0.02310 0.01213 -0.0473 0.9948 0.8103 0.500 0.0617 0.02319 0.01230 -0.0468 0.9897 0.8461 0.750 0.0877 0.02324 0.01246 -0.0469 0.9842 0.8982 1.000 0.1221 0.02324 0.01251 -0.0494 0.9769 1.0000 1.250 0.1598 0.02375 0.01294 -0.0527 0.9719 1.0000 1.500 0.1972 0.02431 0.01344 -0.0557 0.9670 1.0000 1.750 0.2308 0.02477 0.01388 -0.0579 0.9606 1.0000 2.000 0.2687 0.02538 0.01452 -0.0608 0.9552 1.0000 2.250 0.3002 0.02581 0.01502 -0.0625 0.9475 1.0000 2.500 0.3361 0.02638 0.01568 -0.0649 0.9409 1.0000 2.750 0.3696 0.02688 0.01653 -0.0667 0.9329 1.0000 3.000 0.4024 0.02737 0.01720 -0.0684 0.9243 1.0000 3.250 0.4409 0.02791 0.01798 -0.0710 0.9164 1.0000 3.500 0.4742 0.02834 0.01868 -0.0725 0.9059 1.0000 3.750 0.5078 0.02873 0.01940 -0.0740 0.8944 1.0000 4.000 0.5433 0.02905 0.02026 -0.0756 0.8819 1.0000 4.250 0.5820 0.02923 0.02091 -0.0773 0.8676 1.0000 4.500 0.6207 0.02911 0.02140 -0.0785 0.8489 1.0000 4.750 0.6903 0.02647 0.01466 -0.0708 0.0620 1.0000 5.000 0.7128 0.02837 0.01666 -0.0697 0.0446 1.0000 5.250 0.7404 0.03050 0.01890 -0.0693 0.0382 1.0000 5.500 0.7766 0.03226 0.02096 -0.0700 0.0302 1.0000 5.750 0.8193 0.03517 0.02402 -0.0717 0.0256 1.0000 6.000 0.8592 0.03826 0.02752 -0.0725 0.0245 1.0000 6.250 0.8910 0.04157 0.03129 -0.0723 0.0239 1.0000 6.500 0.9162 0.04504 0.03526 -0.0711 0.0235 1.0000 6.750 0.9357 0.04871 0.03968 -0.0694 0.0234 1.0000 7.000 0.9504 0.05243 0.04389 -0.0673 0.0234 1.0000 7.250 0.9610 0.05622 0.04814 -0.0649 0.0235 1.0000 7.500 0.9678 0.06012 0.05245 -0.0624 0.0237 1.0000 7.750 0.9711 0.06405 0.05675 -0.0600 0.0240 1.0000 8.000 0.9710 0.06802 0.06106 -0.0575 0.0243 1.0000 8.250 0.9676 0.07201 0.06533 -0.0551 0.0245 1.0000 8.500 0.9612 0.07594 0.06951 -0.0528 0.0248 1.0000 8.750 0.9509 0.07973 0.07349 -0.0505 0.0251 1.0000 9.000 0.9384 0.08351 0.07743 -0.0485 0.0253 1.0000 9.250 0.9248 0.08754 0.08159 -0.0473 0.0255 1.0000 9.500 0.9109 0.09193 0.08609 -0.0471 0.0258 1.0000 9.750 0.8980 0.09668 0.09093 -0.0478 0.0260 1.0000 10.000 0.8861 0.10184 0.09615 -0.0494 0.0263 1.0000 10.250 0.8777 0.10735 0.10168 -0.0514 0.0266 1.0000