XFOIL Version 6.96 Calculated polar for: MH 94 16.03% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -0.8186 0.12754 0.12479 -0.0432 1.0000 0.0087 -19.250 -0.8599 0.11578 0.11276 -0.0492 1.0000 0.0084 -19.000 -0.8733 0.10964 0.10654 -0.0522 1.0000 0.0085 -18.750 -0.8891 0.10323 0.10001 -0.0553 1.0000 0.0086 -18.500 -0.9107 0.09613 0.09272 -0.0584 1.0000 0.0084 -18.250 -0.9180 0.09154 0.08807 -0.0605 1.0000 0.0085 -18.000 -0.9303 0.08630 0.08273 -0.0626 1.0000 0.0085 -17.750 -0.9426 0.08125 0.07754 -0.0645 1.0000 0.0084 -17.500 -0.9460 0.07749 0.07376 -0.0661 1.0000 0.0086 -17.250 -0.9551 0.07318 0.06935 -0.0675 1.0000 0.0086 -17.000 -0.9623 0.06927 0.06534 -0.0686 1.0000 0.0086 -16.750 -0.9696 0.06548 0.06145 -0.0695 1.0000 0.0086 -16.500 -0.9723 0.06231 0.05823 -0.0703 1.0000 0.0088 -16.250 -0.9775 0.05901 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0.6920 2.750 0.5166 0.00800 0.00241 -0.0452 0.3518 0.6994 3.000 0.5410 0.00823 0.00252 -0.0445 0.3284 0.7062 3.250 0.5648 0.00842 0.00266 -0.0437 0.3061 0.7137 3.500 0.5892 0.00863 0.00279 -0.0430 0.2855 0.7210 3.750 0.6135 0.00884 0.00292 -0.0423 0.2666 0.7277 4.000 0.6375 0.00903 0.00307 -0.0416 0.2494 0.7349 4.250 0.6616 0.00925 0.00323 -0.0409 0.2329 0.7420 4.500 0.6854 0.00947 0.00338 -0.0401 0.2171 0.7487 4.750 0.7087 0.00969 0.00356 -0.0392 0.2013 0.7560 5.000 0.7321 0.00993 0.00373 -0.0384 0.1864 0.7629 5.500 0.7776 0.01040 0.00411 -0.0365 0.1590 0.7774 5.750 0.7999 0.01065 0.00431 -0.0355 0.1470 0.7843 6.000 0.8210 0.01087 0.00451 -0.0342 0.1364 0.7917 6.250 0.8418 0.01112 0.00473 -0.0329 0.1267 0.7998 6.500 0.8623 0.01139 0.00496 -0.0315 0.1184 0.8072 6.750 0.8835 0.01160 0.00520 -0.0303 0.1129 0.8152 7.250 0.9246 0.01212 0.00572 -0.0276 0.1035 0.8317 7.500 0.9459 0.01235 0.00596 -0.0264 0.1007 0.8405 7.750 0.9656 0.01260 0.00624 -0.0249 0.0976 0.8495 8.000 0.9844 0.01294 0.00658 -0.0234 0.0940 0.8595 8.250 1.0044 0.01314 0.00685 -0.0219 0.0926 0.8698 8.500 1.0246 0.01336 0.00711 -0.0206 0.0907 0.8806 8.750 1.0431 0.01361 0.00741 -0.0190 0.0888 0.8935 9.000 1.0602 0.01388 0.00772 -0.0171 0.0870 0.9086 9.500 1.0945 0.01449 0.00848 -0.0134 0.0833 0.9632 9.750 1.1244 0.01479 0.00883 -0.0144 0.0823 1.0000 10.000 1.1451 0.01512 0.00916 -0.0135 0.0811 1.0000 10.250 1.1646 0.01547 0.00954 -0.0123 0.0799 1.0000 10.500 1.1833 0.01587 0.00993 -0.0111 0.0785 1.0000 10.750 1.2008 0.01633 0.01038 -0.0097 0.0771 1.0000 11.000 1.2153 0.01691 0.01098 -0.0080 0.0757 1.0000 11.250 1.2297 0.01751 0.01162 -0.0062 0.0746 1.0000 11.500 1.2482 0.01791 0.01205 -0.0051 0.0740 1.0000 11.750 1.2656 0.01837 0.01254 -0.0038 0.0734 1.0000 12.000 1.2824 0.01885 0.01307 -0.0025 0.0726 1.0000 12.250 1.2987 0.01937 0.01362 -0.0012 0.0717 1.0000 12.500 1.3142 0.01995 0.01422 0.0001 0.0709 1.0000 12.750 1.3291 0.02056 0.01486 0.0015 0.0701 1.0000 13.000 1.3430 0.02124 0.01556 0.0029 0.0692 1.0000 13.250 1.3542 0.02208 0.01643 0.0046 0.0683 1.0000 13.500 1.3614 0.02318 0.01757 0.0066 0.0673 1.0000 13.750 1.3695 0.02427 0.01871 0.0083 0.0665 1.0000 14.000 1.3849 0.02494 0.01944 0.0093 0.0661 1.0000 14.250 1.3983 0.02576 0.02031 0.0104 0.0656 1.0000 14.500 1.4106 0.02667 0.02127 0.0115 0.0651 1.0000 14.750 1.4221 0.02765 0.02230 0.0126 0.0645 1.0000 15.000 1.4339 0.02864 0.02334 0.0136 0.0637 1.0000 15.250 1.4433 0.02984 0.02460 0.0146 0.0633 1.0000 15.500 1.4533 0.03103 0.02583 0.0155 0.0626 1.0000 15.750 1.4624 0.03232 0.02716 0.0163 0.0620 1.0000 16.000 1.4696 0.03382 0.02871 0.0171 0.0614 1.0000 16.250 1.4737 0.03562 0.03056 0.0180 0.0607 1.0000 16.500 1.4742 0.03781 0.03281 0.0187 0.0599 1.0000 16.750 1.4746 0.04009 0.03516 0.0194 0.0593 1.0000 17.000 1.4835 0.04168 0.03683 0.0195 0.0590 1.0000 17.250 1.4907 0.04350 0.03872 0.0197 0.0586 1.0000 17.500 1.4975 0.04540 0.04069 0.0197 0.0581 1.0000 17.750 1.5033 0.04744 0.04282 0.0196 0.0576 1.0000 18.000 1.5075 0.04971 0.04515 0.0194 0.0571 1.0000 18.250 1.5106 0.05216 0.04767 0.0190 0.0566 1.0000 18.500 1.5134 0.05471 0.05030 0.0186 0.0561 1.0000 18.750 1.5150 0.05747 0.05313 0.0179 0.0556 1.0000 19.000 1.5157 0.06039 0.05611 0.0171 0.0551 1.0000 19.250 1.5146 0.06361 0.05939 0.0161 0.0545 1.0000