XFOIL Version 6.96 Calculated polar for: EPPLER E836 HYDROFOIL 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.6579 0.06203 0.05724 -0.0477 1.0000 0.0604 -10.250 -0.6763 0.05749 0.05260 -0.0471 1.0000 0.0592 -10.000 -0.6974 0.05330 0.04829 -0.0455 1.0000 0.0577 -9.750 -0.7809 0.06073 0.05527 -0.0387 1.0000 0.0586 -9.500 -0.8009 0.05596 0.05014 -0.0350 1.0000 0.0541 -9.250 -0.8126 0.05250 0.04607 -0.0304 1.0000 0.0489 -9.000 -0.8130 0.04885 0.04218 -0.0276 1.0000 0.0481 -8.750 -0.8139 0.04607 0.03906 -0.0242 1.0000 0.0484 -8.500 -0.8134 0.04343 0.03609 -0.0205 1.0000 0.0486 -8.250 -0.8113 0.04092 0.03328 -0.0167 1.0000 0.0486 -8.000 -0.8089 0.03867 0.03071 -0.0128 1.0000 0.0488 -7.750 -0.8039 0.03630 0.02803 -0.0090 1.0000 0.0487 -7.500 -0.7953 0.03415 0.02556 -0.0057 1.0000 0.0489 -7.250 -0.7836 0.03228 0.02337 -0.0027 1.0000 0.0497 -7.000 -0.7634 0.02973 0.02064 -0.0012 1.0000 0.0512 -6.750 -0.7485 0.02805 0.01899 0.0005 1.0000 0.0563 -6.500 -0.7339 0.02691 0.01766 0.0030 1.0000 0.0618 -6.250 -0.7184 0.02507 0.01596 0.0051 1.0000 0.0673 -6.000 -0.7085 0.02406 0.01491 0.0080 1.0000 0.0766 -5.750 -0.7018 0.02290 0.01382 0.0114 1.0000 0.0892 -5.500 -0.6982 0.02155 0.01268 0.0152 1.0000 0.1103 -5.250 -0.7025 0.01932 0.01131 0.0201 1.0000 0.1994 -5.000 -0.7125 0.01695 0.01043 0.0258 1.0000 0.4176 -4.750 -0.7095 0.01648 0.01093 0.0313 1.0000 0.6007 -4.500 -0.6987 0.01705 0.01162 0.0359 1.0000 0.6799 -4.250 -0.6877 0.01793 0.01241 0.0406 1.0000 0.7286 -4.000 -0.6746 0.01876 0.01315 0.0449 1.0000 0.7597 -3.750 -0.6594 0.01958 0.01385 0.0488 1.0000 0.7835 -3.500 -0.6441 0.02025 0.01440 0.0525 1.0000 0.8046 -3.250 -0.6150 0.02115 0.01514 0.0536 0.9967 0.8246 -3.000 -0.5833 0.02186 0.01563 0.0536 0.9923 0.8437 -2.750 -0.5430 0.02272 0.01630 0.0523 0.9884 0.8591 -2.500 -0.4966 0.02351 0.01689 0.0494 0.9850 0.8729 -2.250 -0.4495 0.02414 0.01730 0.0459 0.9817 0.8856 -2.000 -0.3788 0.02493 0.01789 0.0380 0.9802 0.8924 -1.750 -0.3322 0.02514 0.01797 0.0337 0.9763 0.9017 -1.500 -0.2712 0.02545 0.01811 0.0267 0.9735 0.9078 -1.250 -0.2228 0.02562 0.01818 0.0217 0.9699 0.9156 -1.000 -0.1755 0.02567 0.01814 0.0170 0.9657 0.9218 -0.750 -0.1371 0.02569 0.01810 0.0138 0.9603 0.9293 -0.500 -0.0806 0.02577 0.01813 0.0073 0.9570 0.9340 -0.250 -0.0537 0.02577 0.01811 0.0061 0.9503 0.9419 0.000 -0.0001 0.02574 0.01807 0.0000 0.9459 0.9459 0.250 0.0532 0.02577 0.01811 -0.0061 0.9420 0.9504 0.500 0.0806 0.02577 0.01813 -0.0073 0.9340 0.9570 0.750 0.1371 0.02569 0.01810 -0.0139 0.9294 0.9603 1.000 0.1753 0.02568 0.01814 -0.0170 0.9219 0.9657 1.250 0.2230 0.02562 0.01817 -0.0218 0.9156 0.9699 1.500 0.2712 0.02545 0.01811 -0.0267 0.9078 0.9735 1.750 0.3322 0.02514 0.01797 -0.0337 0.9017 0.9763 2.000 0.3789 0.02493 0.01789 -0.0380 0.8923 0.9802 2.250 0.4494 0.02415 0.01731 -0.0459 0.8856 0.9817 2.500 0.4970 0.02350 0.01689 -0.0495 0.8729 0.9850 2.750 0.5429 0.02273 0.01631 -0.0524 0.8591 0.9884 3.000 0.5835 0.02185 0.01562 -0.0537 0.8437 0.9922 3.250 0.6150 0.02114 0.01513 -0.0536 0.8244 0.9967 3.500 0.6444 0.02023 0.01439 -0.0525 0.8045 1.0000 3.750 0.6596 0.01957 0.01385 -0.0488 0.7833 1.0000 4.000 0.6749 0.01876 0.01315 -0.0449 0.7597 1.0000 4.250 0.6877 0.01792 0.01240 -0.0406 0.7279 1.0000 4.500 0.6990 0.01704 0.01160 -0.0359 0.6792 1.0000 4.750 0.7098 0.01647 0.01092 -0.0314 0.5999 1.0000 5.000 0.7126 0.01697 0.01043 -0.0258 0.4150 1.0000 5.250 0.7027 0.01933 0.01131 -0.0201 0.1991 1.0000 5.500 0.6984 0.02155 0.01268 -0.0153 0.1101 1.0000 5.750 0.7012 0.02299 0.01389 -0.0113 0.0885 1.0000 6.000 0.7086 0.02409 0.01493 -0.0081 0.0765 1.0000 6.250 0.7185 0.02509 0.01597 -0.0051 0.0671 1.0000 6.500 0.7341 0.02691 0.01767 -0.0030 0.0615 1.0000 6.750 0.7490 0.02806 0.01900 -0.0006 0.0565 1.0000 7.000 0.7653 0.03003 0.02092 0.0009 0.0508 1.0000 7.250 0.7837 0.03227 0.02337 0.0027 0.0496 1.0000 7.500 0.7957 0.03418 0.02560 0.0057 0.0489 1.0000 7.750 0.8039 0.03633 0.02807 0.0090 0.0486 1.0000 8.000 0.8093 0.03870 0.03074 0.0127 0.0488 1.0000 8.250 0.8121 0.04106 0.03341 0.0166 0.0489 1.0000 8.500 0.8138 0.04349 0.03615 0.0204 0.0488 1.0000 8.750 0.8140 0.04602 0.03902 0.0242 0.0484 1.0000 9.000 0.8127 0.04879 0.04213 0.0277 0.0480 1.0000 9.250 0.8130 0.05245 0.04602 0.0303 0.0490 1.0000 9.500 0.8007 0.05597 0.05015 0.0351 0.0539 1.0000 9.750 0.7807 0.06075 0.05529 0.0387 0.0587 1.0000 10.000 0.6973 0.05322 0.04820 0.0456 0.0580 1.0000 10.250 0.6741 0.05722 0.05234 0.0473 0.0587 1.0000 10.500 0.6557 0.06191 0.05713 0.0478 0.0603 1.0000 10.750 0.5875 0.10096 0.09624 0.0228 0.1475 1.0000