XFOIL Version 6.96 Calculated polar for: EPPLER E838 HYDROFOIL AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.8355 0.12340 0.12050 -0.0210 1.0000 0.0099 -18.250 -0.8607 0.11406 0.11097 -0.0262 1.0000 0.0098 -18.000 -0.8818 0.10601 0.10275 -0.0305 1.0000 0.0097 -17.750 -0.8975 0.09936 0.09595 -0.0338 1.0000 0.0096 -17.500 -0.9141 0.09276 0.08916 -0.0370 1.0000 0.0096 -17.250 -0.9274 0.08702 0.08324 -0.0395 1.0000 0.0097 -17.000 -0.9399 0.08166 0.07770 -0.0415 1.0000 0.0097 -16.750 -0.9490 0.07698 0.07286 -0.0429 1.0000 0.0096 -16.500 -0.9595 0.07226 0.06793 -0.0443 1.0000 0.0098 -16.250 -0.9647 0.06841 0.06392 -0.0451 1.0000 0.0098 -16.000 -0.9690 0.06482 0.06015 -0.0457 1.0000 0.0099 -15.750 -0.9718 0.06170 0.05687 -0.0465 1.0000 0.0100 -15.500 -0.9701 0.05886 0.05389 -0.0465 1.0000 0.0100 -15.250 -0.9699 0.05577 0.05062 -0.0457 1.0000 0.0103 -15.000 -0.9641 0.05359 0.04834 -0.0454 1.0000 0.0104 -14.750 -0.9578 0.05154 0.04623 -0.0450 1.0000 0.0106 -14.500 -0.9513 0.04963 0.04429 -0.0450 1.0000 0.0111 -14.250 -0.9436 0.04780 0.04237 -0.0445 1.0000 0.0112 -14.000 -0.9355 0.04607 0.04059 -0.0444 1.0000 0.0116 -13.750 -0.9266 0.04442 0.03886 -0.0437 1.0000 0.0116 -13.500 -0.9176 0.04284 0.03722 -0.0434 1.0000 0.0121 -13.250 -0.9084 0.04129 0.03560 -0.0428 1.0000 0.0126 -13.000 -0.8984 0.03985 0.03409 -0.0423 1.0000 0.0129 -12.750 -0.8876 0.03849 0.03267 -0.0418 1.0000 0.0132 -12.500 -0.8823 0.03674 0.03087 -0.0408 1.0000 0.0137 -12.250 -0.8774 0.03501 0.02911 -0.0399 1.0000 0.0144 -12.000 -0.8692 0.03354 0.02764 -0.0393 1.0000 0.0150 -11.750 -0.8275 0.03191 0.02588 -0.0455 0.9228 0.0166 -11.500 -0.8104 0.03083 0.02455 -0.0459 0.8798 0.0174 -11.250 -0.8117 0.02915 0.02270 -0.0438 0.8574 0.0183 -11.000 -0.8077 0.02780 0.02125 -0.0421 0.8426 0.0194 -10.750 -0.7994 0.02671 0.02007 -0.0408 0.8315 0.0205 -10.500 -0.7908 0.02565 0.01889 -0.0394 0.8220 0.0216 -10.250 -0.7819 0.02458 0.01773 -0.0380 0.8135 0.0231 -10.000 -0.7780 0.02329 0.01638 -0.0361 0.8060 0.0259 -9.750 -0.7675 0.02234 0.01537 -0.0348 0.7990 0.0280 -9.500 -0.7596 0.02131 0.01428 -0.0331 0.7927 0.0314 -9.250 -0.7512 0.02032 0.01326 -0.0314 0.7872 0.0366 -9.000 -0.7451 0.01923 0.01219 -0.0295 0.7814 0.0452 -8.750 -0.7410 0.01813 0.01112 -0.0271 0.7762 0.0605 -8.500 -0.7385 0.01699 0.01009 -0.0245 0.7710 0.0838 -8.250 -0.7373 0.01588 0.00912 -0.0215 0.7658 0.1113 -8.000 -0.7390 0.01481 0.00819 -0.0178 0.7614 0.1457 -7.750 -0.7423 0.01383 0.00739 -0.0134 0.7571 0.1851 -7.500 -0.7486 0.01297 0.00676 -0.0081 0.7524 0.2326 -7.250 -0.7497 0.01198 0.00606 -0.0037 0.7483 0.2953 -7.000 -0.7504 0.01092 0.00536 0.0006 0.7447 0.3754 -6.750 -0.7410 0.01018 0.00494 0.0035 0.7410 0.4468 -6.500 -0.7219 0.00986 0.00474 0.0048 0.7374 0.4886 -6.250 -0.6988 0.00971 0.00460 0.0054 0.7341 0.5127 -6.000 -0.6740 0.00965 0.00449 0.0058 0.7310 0.5312 -5.750 -0.6486 0.00964 0.00443 0.0061 0.7279 0.5474 -5.500 -0.6228 0.00965 0.00441 0.0064 0.7245 0.5624 -5.250 -0.5960 0.00966 0.00441 0.0064 0.7214 0.5726 -5.000 -0.5690 0.00968 0.00435 0.0064 0.7184 0.5809 -4.750 -0.5420 0.00977 0.00437 0.0065 0.7156 0.5904 -4.500 -0.5145 0.00986 0.00443 0.0064 0.7127 0.5984 -4.250 -0.4870 0.00992 0.00445 0.0064 0.7095 0.6058 -4.000 -0.4589 0.00994 0.00444 0.0062 0.7065 0.6115 -3.750 -0.4303 0.00999 0.00446 0.0059 0.7037 0.6165 -3.500 -0.4024 0.01001 0.00439 0.0057 0.7010 0.6212 -3.250 -0.3740 0.01002 0.00432 0.0054 0.6983 0.6248 -3.000 -0.3450 0.00998 0.00431 0.0049 0.6954 0.6278 -2.750 -0.3162 0.00997 0.00428 0.0045 0.6924 0.6309 -2.500 -0.2877 0.00995 0.00421 0.0041 0.6896 0.6342 -2.250 -0.2595 0.00995 0.00412 0.0038 0.6869 0.6375 -2.000 -0.2305 0.00991 0.00405 0.0034 0.6843 0.6401 -1.750 -0.2015 0.00990 0.00405 0.0029 0.6816 0.6427 -1.500 -0.1727 0.00988 0.00404 0.0025 0.6787 0.6454 -1.250 -0.1440 0.00988 0.00402 0.0021 0.6758 0.6485 -1.000 -0.1154 0.00988 0.00396 0.0017 0.6730 0.6517 -0.750 -0.0866 0.00984 0.00389 0.0013 0.6705 0.6543 -0.500 -0.0575 0.00987 0.00390 0.0008 0.6680 0.6566 -0.250 -0.0287 0.00985 0.00394 0.0004 0.6652 0.6593 0.000 0.0000 0.00985 0.00395 0.0000 0.6622 0.6623 0.250 0.0287 0.00985 0.00394 -0.0004 0.6593 0.6653 0.500 0.0575 0.00987 0.00390 -0.0008 0.6566 0.6680 0.750 0.0866 0.00984 0.00389 -0.0013 0.6542 0.6705 1.000 0.1154 0.00987 0.00396 -0.0017 0.6516 0.6731 1.250 0.1440 0.00988 0.00402 -0.0021 0.6484 0.6759 1.500 0.1727 0.00989 0.00404 -0.0025 0.6453 0.6788 1.750 0.2015 0.00990 0.00405 -0.0029 0.6426 0.6817 2.000 0.2305 0.00991 0.00405 -0.0034 0.6401 0.6844 2.250 0.2594 0.00995 0.00412 -0.0038 0.6374 0.6869 2.500 0.2877 0.00995 0.00421 -0.0041 0.6342 0.6896 2.750 0.3162 0.00997 0.00428 -0.0045 0.6309 0.6924 3.000 0.3450 0.00998 0.00431 -0.0049 0.6278 0.6954 3.250 0.3740 0.01002 0.00433 -0.0054 0.6248 0.6983 3.500 0.4023 0.01002 0.00440 -0.0057 0.6212 0.7010 3.750 0.4302 0.00999 0.00446 -0.0059 0.6165 0.7037 4.000 0.4588 0.00995 0.00445 -0.0062 0.6115 0.7065 4.250 0.4870 0.00993 0.00445 -0.0064 0.6059 0.7096 4.500 0.5144 0.00986 0.00443 -0.0064 0.5984 0.7128 4.750 0.5419 0.00977 0.00437 -0.0065 0.5904 0.7157 5.000 0.5689 0.00968 0.00435 -0.0064 0.5809 0.7184 5.250 0.5960 0.00966 0.00441 -0.0064 0.5726 0.7214 5.500 0.6228 0.00965 0.00441 -0.0064 0.5624 0.7246 5.750 0.6485 0.00964 0.00443 -0.0061 0.5475 0.7280 6.000 0.6740 0.00965 0.00449 -0.0058 0.5316 0.7311 6.250 0.6988 0.00971 0.00461 -0.0055 0.5133 0.7341 6.500 0.7218 0.00986 0.00474 -0.0048 0.4884 0.7375 6.750 0.7406 0.01019 0.00494 -0.0034 0.4458 0.7410 7.000 0.7499 0.01093 0.00536 -0.0006 0.3744 0.7447 7.250 0.7501 0.01196 0.00605 0.0036 0.2970 0.7484 7.500 0.7479 0.01299 0.00677 0.0082 0.2313 0.7525 7.750 0.7420 0.01384 0.00739 0.0134 0.1847 0.7571 8.000 0.7386 0.01483 0.00820 0.0178 0.1448 0.7614 8.250 0.7374 0.01588 0.00911 0.0215 0.1114 0.7659 8.500 0.7382 0.01700 0.01010 0.0245 0.0833 0.7711 8.750 0.7415 0.01810 0.01110 0.0271 0.0610 0.7762 9.000 0.7452 0.01922 0.01219 0.0295 0.0451 0.7814 9.250 0.7511 0.02033 0.01327 0.0315 0.0365 0.7872 9.500 0.7605 0.02126 0.01423 0.0330 0.0318 0.7928 9.750 0.7669 0.02239 0.01542 0.0349 0.0286 0.7991 10.000 0.7777 0.02331 0.01640 0.0362 0.0260 0.8061 10.250 0.7840 0.02446 0.01762 0.0379 0.0236 0.8136 10.500 0.7894 0.02575 0.01899 0.0395 0.0221 0.8221 10.750 0.7996 0.02670 0.02007 0.0408 0.0206 0.8315 11.000 0.8089 0.02772 0.02117 0.0420 0.0192 0.8427 11.250 0.8127 0.02908 0.02264 0.0437 0.0183 0.8576 11.500 0.8132 0.03066 0.02437 0.0457 0.0172 0.8799 11.750 0.8290 0.03186 0.02583 0.0453 0.0164 0.9236 12.000 0.8710 0.03344 0.02751 0.0391 0.0147 1.0000 12.250 0.8789 0.03493 0.02902 0.0397 0.0143 1.0000 12.500 0.8833 0.03670 0.03082 0.0407 0.0138 1.0000 12.750 0.8881 0.03847 0.03264 0.0418 0.0133 1.0000 13.000 0.8994 0.03980 0.03405 0.0422 0.0129 1.0000 13.250 0.9094 0.04126 0.03558 0.0427 0.0122 1.0000 13.500 0.9187 0.04279 0.03716 0.0432 0.0120 1.0000 13.750 0.9279 0.04436 0.03880 0.0437 0.0118 1.0000 14.000 0.9366 0.04602 0.04053 0.0441 0.0115 1.0000 14.250 0.9446 0.04775 0.04231 0.0443 0.0110 1.0000 14.500 0.9517 0.04959 0.04417 0.0444 0.0106 1.0000 14.750 0.9592 0.05148 0.04618 0.0449 0.0107 1.0000 15.000 0.9655 0.05351 0.04825 0.0452 0.0104 1.0000 15.250 0.9709 0.05575 0.05060 0.0457 0.0102 1.0000 15.500 0.9737 0.05850 0.05350 0.0463 0.0101 1.0000 15.750 0.9706 0.06171 0.05689 0.0459 0.0099 1.0000 16.000 0.9706 0.06481 0.06014 0.0458 0.0100 1.0000 16.250 0.9661 0.06837 0.06387 0.0450 0.0098 1.0000 16.500 0.9608 0.07221 0.06788 0.0442 0.0098 1.0000 16.750 0.9517 0.07671 0.07257 0.0429 0.0097 1.0000 17.000 0.9423 0.08143 0.07746 0.0414 0.0097 1.0000 17.250 0.9286 0.08700 0.08323 0.0392 0.0096 1.0000 17.500 0.9147 0.09282 0.08921 0.0369 0.0097 1.0000 17.750 0.8964 0.09974 0.09634 0.0335 0.0096 1.0000 18.000 0.8794 0.10672 0.10349 0.0299 0.0096 1.0000 18.250 0.8609 0.11432 0.11125 0.0258 0.0097 1.0000 18.500 0.8422 0.12248 0.11958 0.0211 0.0097 1.0000 18.750 0.8121 0.13329 0.13055 0.0151 0.0099 1.0000