XFOIL Version 6.96 Calculated polar for: EPPLER 817 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 ------ -------- --------- --------- -------- -------- -------- -10.750 -0.4950 0.10267 0.09580 -0.0510 1.0000 0.0298 -10.500 -0.5055 0.09759 0.09080 -0.0521 1.0000 0.0295 -10.250 -0.5199 0.09204 0.08533 -0.0535 1.0000 0.0292 -10.000 -0.5330 0.08738 0.08072 -0.0545 1.0000 0.0283 -9.750 -0.5520 0.08217 0.07554 -0.0559 1.0000 0.0279 -9.500 -0.5723 0.07750 0.07089 -0.0569 1.0000 0.0274 -9.250 -0.5944 0.07343 0.06682 -0.0573 1.0000 0.0270 -9.000 -0.6194 0.06993 0.06331 -0.0569 1.0000 0.0267 -8.750 -0.6448 0.06697 0.06032 -0.0558 1.0000 0.0264 -8.500 -0.6632 0.06346 0.05670 -0.0557 1.0000 0.0261 -8.250 -0.6766 0.05977 0.05279 -0.0554 1.0000 0.0261 -8.000 -0.6837 0.05597 0.04871 -0.0550 1.0000 0.0262 -7.750 -0.6843 0.05225 0.04464 -0.0547 1.0000 0.0265 -7.500 -0.6791 0.04868 0.04065 -0.0544 1.0000 0.0272 -7.250 -0.6688 0.04558 0.03711 -0.0539 1.0000 0.0288 -7.000 -0.6542 0.04290 0.03377 -0.0536 1.0000 0.0319 -6.750 -0.6403 0.04019 0.03104 -0.0530 1.0000 0.0349 -6.500 -0.6230 0.03804 0.02865 -0.0520 1.0000 0.0382 -6.250 -0.6045 0.03607 0.02636 -0.0506 1.0000 0.0416 -6.000 -0.5865 0.03398 0.02415 -0.0497 1.0000 0.0475 -5.750 -0.5665 0.03205 0.02213 -0.0499 1.0000 0.0618 -5.500 -0.5437 0.02975 0.01971 -0.0504 1.0000 0.0802 -5.250 -0.5168 0.02664 0.01720 -0.0533 1.0000 0.1450 -5.000 -0.4902 0.02531 0.01658 -0.0550 1.0000 0.2967 -4.750 -0.4667 0.02539 0.01657 -0.0546 1.0000 0.3575 -4.500 -0.4444 0.02566 0.01654 -0.0537 1.0000 0.4013 -4.250 -0.4234 0.02592 0.01669 -0.0523 1.0000 0.4326 -4.000 -0.4011 0.02593 0.01650 -0.0514 1.0000 0.4552 -3.750 -0.3780 0.02579 0.01614 -0.0508 1.0000 0.4714 -3.500 -0.3547 0.02563 0.01577 -0.0503 1.0000 0.4856 -3.250 -0.3310 0.02547 0.01541 -0.0499 1.0000 0.4992 -3.000 -0.3074 0.02533 0.01510 -0.0495 1.0000 0.5127 -2.750 -0.2838 0.02522 0.01483 -0.0491 1.0000 0.5263 -2.500 -0.2604 0.02515 0.01461 -0.0488 1.0000 0.5399 -2.250 -0.2369 0.02511 0.01436 -0.0484 1.0000 0.5539 -2.000 -0.2137 0.02510 0.01424 -0.0480 1.0000 0.5681 -1.750 -0.1874 0.02517 0.01421 -0.0482 0.9984 0.5830 -1.500 -0.1576 0.02537 0.01432 -0.0490 0.9952 0.5991 -1.250 -0.1279 0.02556 0.01443 -0.0499 0.9919 0.6159 -1.000 -0.0991 0.02574 0.01449 -0.0506 0.9882 0.6331 -0.750 -0.0703 0.02599 0.01473 -0.0512 0.9844 0.6500 -0.500 -0.0399 0.02631 0.01503 -0.0522 0.9810 0.6683 -0.250 -0.0132 0.02647 0.01519 -0.0525 0.9765 0.6871 0.000 0.0146 0.02672 0.01545 -0.0529 0.9720 0.7058 0.250 0.0448 0.02705 0.01580 -0.0538 0.9680 0.7270 0.500 0.0686 0.02718 0.01600 -0.0534 0.9625 0.7468 0.750 0.0969 0.02746 0.01635 -0.0538 0.9576 0.7697 1.000 0.1218 0.02764 0.01662 -0.0536 0.9521 0.7942 1.250 0.1466 0.02781 0.01691 -0.0533 0.9461 0.8210 1.500 0.1709 0.02795 0.01717 -0.0528 0.9402 0.8525 1.750 0.1960 0.02799 0.01736 -0.0526 0.9333 0.8958 2.000 0.2293 0.02795 0.01746 -0.0546 0.9252 1.0000 2.250 0.2678 0.02847 0.01802 -0.0579 0.9190 1.0000 2.500 0.3017 0.02893 0.01851 -0.0602 0.9117 1.0000 2.750 0.3395 0.02946 0.01909 -0.0630 0.9049 1.0000 3.000 0.3703 0.02989 0.01960 -0.0644 0.8959 1.0000 3.250 0.4070 0.03036 0.02018 -0.0668 0.8881 1.0000 3.500 0.4413 0.03077 0.02081 -0.0685 0.8787 1.0000 3.750 0.4724 0.03113 0.02134 -0.0697 0.8678 1.0000 4.000 0.5052 0.03145 0.02186 -0.0709 0.8566 1.0000 4.250 0.5393 0.03169 0.02233 -0.0722 0.8444 1.0000 4.500 0.5737 0.03178 0.02270 -0.0733 0.8307 1.0000 4.750 0.6106 0.03162 0.02297 -0.0744 0.8147 1.0000 5.000 0.6473 0.03106 0.02278 -0.0748 0.7941 1.0000 5.250 0.6833 0.02968 0.02180 -0.0738 0.7617 1.0000 5.500 0.7094 0.02799 0.02044 -0.0706 0.7121 1.0000 5.750 0.7399 0.02587 0.01858 -0.0670 0.6246 1.0000 6.000 0.7805 0.02622 0.01643 -0.0641 0.2294 1.0000 6.250 0.7866 0.02894 0.01817 -0.0616 0.1259 1.0000 6.500 0.8027 0.03119 0.02008 -0.0601 0.0873 1.0000 6.750 0.8245 0.03318 0.02194 -0.0594 0.0624 1.0000 7.000 0.8645 0.03562 0.02469 -0.0604 0.0489 1.0000 7.250 0.9061 0.03827 0.02742 -0.0624 0.0377 1.0000 7.500 0.9506 0.04137 0.03107 -0.0639 0.0326 1.0000 7.750 0.9838 0.04486 0.03498 -0.0643 0.0305 1.0000 8.000 1.0071 0.04835 0.03889 -0.0635 0.0293 1.0000 8.250 1.0227 0.05167 0.04255 -0.0621 0.0280 1.0000 8.500 1.0323 0.05549 0.04662 -0.0605 0.0267 1.0000 8.750 1.0360 0.05918 0.05073 -0.0578 0.0259 1.0000 9.000 1.0358 0.06251 0.05455 -0.0547 0.0254 1.0000 9.250 1.0311 0.06600 0.05846 -0.0515 0.0249 1.0000 9.500 1.0213 0.06937 0.06218 -0.0481 0.0246 1.0000 9.750 1.0086 0.07293 0.06602 -0.0450 0.0245 1.0000 10.000 0.9936 0.07670 0.07005 -0.0426 0.0244 1.0000 10.250 0.9772 0.08077 0.07434 -0.0410 0.0245 1.0000 10.500 0.9600 0.08522 0.07898 -0.0403 0.0246 1.0000 10.750 0.9422 0.09012 0.08405 -0.0406 0.0248 1.0000 11.000 0.9245 0.09554 0.08960 -0.0420 0.0251 1.0000 11.250 0.9080 0.10152 0.09567 -0.0445 0.0253 1.0000