XFOIL Version 6.96 Calculated polar for: WORTMANN FX 66-17A-175 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.4156 0.06184 0.05773 -0.0951 0.6195 0.0045 -12.500 -0.4491 0.05392 0.04960 -0.0997 0.6166 0.0044 -12.250 -0.4578 0.05009 0.04564 -0.1018 0.6116 0.0045 -12.000 -0.4834 0.04445 0.03977 -0.1042 0.6075 0.0045 -11.750 -0.4848 0.04189 0.03710 -0.1053 0.6019 0.0046 -11.500 -0.4964 0.03825 0.03325 -0.1063 0.5969 0.0045 -11.250 -0.4948 0.03614 0.03103 -0.1070 0.5915 0.0047 -11.000 -0.5016 0.03318 0.02785 -0.1073 0.5864 0.0047 -10.750 -0.5009 0.03112 0.02564 -0.1075 0.5815 0.0049 -10.500 -0.5038 0.02893 0.02327 -0.1070 0.5770 0.0049 -10.250 -0.5052 0.02742 0.02158 -0.1051 0.5723 0.0050 -10.000 -0.4975 0.02604 0.02000 -0.1039 0.5678 0.0052 -9.750 -0.4862 0.02472 0.01851 -0.1028 0.5634 0.0053 -9.500 -0.4723 0.02357 0.01718 -0.1018 0.5588 0.0055 -9.250 -0.4563 0.02255 0.01600 -0.1009 0.5548 0.0057 -9.000 -0.4376 0.02173 0.01502 -0.1002 0.5510 0.0059 -8.750 -0.4182 0.02094 0.01409 -0.0996 0.5472 0.0060 -8.500 -0.4007 0.01995 0.01303 -0.0988 0.5435 0.0066 -8.000 -0.3575 0.01877 0.01169 -0.0979 0.5369 0.0072 -7.750 -0.3358 0.01810 0.01094 -0.0974 0.5336 0.0075 -7.500 -0.3137 0.01746 0.01020 -0.0969 0.5302 0.0080 -7.250 -0.2913 0.01687 0.00949 -0.0964 0.5271 0.0083 -7.000 -0.2681 0.01633 0.00884 -0.0959 0.5243 0.0087 -6.750 -0.2440 0.01584 0.00827 -0.0956 0.5215 0.0090 -6.500 -0.2217 0.01511 0.00745 -0.0951 0.5186 0.0095 -6.250 -0.1972 0.01468 0.00697 -0.0949 0.5156 0.0104 -6.000 -0.1721 0.01432 0.00654 -0.0946 0.5128 0.0112 -5.750 -0.1467 0.01397 0.00610 -0.0944 0.5102 0.0121 -5.500 -0.1207 0.01362 0.00567 -0.0943 0.5074 0.0129 -5.250 -0.0949 0.01324 0.00522 -0.0941 0.5045 0.0142 -5.000 -0.0687 0.01294 0.00487 -0.0940 0.5018 0.0160 -4.750 -0.0421 0.01272 0.00458 -0.0939 0.4994 0.0186 -4.500 -0.0158 0.01246 0.00428 -0.0938 0.4971 0.0260 -4.250 0.0106 0.01212 0.00400 -0.0938 0.4950 0.0452 -4.000 0.0368 0.01173 0.00372 -0.0938 0.4927 0.0800 -3.750 0.0622 0.01122 0.00342 -0.0938 0.4903 0.1444 -3.500 0.0862 0.01044 0.00303 -0.0938 0.4880 0.2613 -3.250 0.1103 0.00984 0.00292 -0.0936 0.4858 0.4025 -3.000 0.1384 0.00991 0.00296 -0.0937 0.4837 0.4349 -2.750 0.1667 0.01000 0.00300 -0.0937 0.4818 0.4512 -2.500 0.1953 0.01009 0.00305 -0.0938 0.4798 0.4641 -2.250 0.2239 0.01020 0.00308 -0.0940 0.4776 0.4737 -2.000 0.2522 0.01024 0.00310 -0.0940 0.4755 0.4795 -1.750 0.2805 0.01027 0.00308 -0.0942 0.4734 0.4827 -1.500 0.3088 0.01032 0.00305 -0.0943 0.4714 0.4858 -1.250 0.3371 0.01036 0.00301 -0.0944 0.4696 0.4882 -1.000 0.3652 0.01039 0.00298 -0.0945 0.4678 0.4897 -0.750 0.3936 0.01039 0.00297 -0.0947 0.4661 0.4910 -0.500 0.4219 0.01040 0.00296 -0.0949 0.4642 0.4923 -0.250 0.4502 0.01042 0.00296 -0.0950 0.4621 0.4936 0.000 0.4783 0.01045 0.00296 -0.0952 0.4601 0.4950 0.250 0.5063 0.01049 0.00296 -0.0953 0.4581 0.4965 0.500 0.5342 0.01054 0.00298 -0.0954 0.4563 0.4980 0.750 0.5620 0.01061 0.00300 -0.0955 0.4545 0.4994 1.000 0.5901 0.01065 0.00304 -0.0957 0.4527 0.5009 1.250 0.6182 0.01070 0.00308 -0.0958 0.4508 0.5024 1.500 0.6462 0.01074 0.00312 -0.0960 0.4488 0.5040 1.750 0.6739 0.01078 0.00318 -0.0961 0.4468 0.5055 2.000 0.7016 0.01083 0.00324 -0.0962 0.4450 0.5071 2.250 0.7292 0.01090 0.00331 -0.0963 0.4433 0.5086 2.500 0.7566 0.01098 0.00339 -0.0963 0.4417 0.5101 2.750 0.7839 0.01108 0.00348 -0.0964 0.4400 0.5117 3.000 0.8116 0.01115 0.00357 -0.0965 0.4385 0.5134 3.250 0.8392 0.01121 0.00367 -0.0966 0.4369 0.5153 3.500 0.8668 0.01129 0.00379 -0.0967 0.4352 0.5173 3.750 0.8942 0.01137 0.00390 -0.0968 0.4337 0.5194 4.000 0.9213 0.01144 0.00403 -0.0969 0.4321 0.5215 4.250 0.9484 0.01153 0.00416 -0.0969 0.4306 0.5235 4.500 0.9754 0.01163 0.00430 -0.0970 0.4292 0.5256 4.750 1.0023 0.01174 0.00443 -0.0970 0.4278 0.5277 5.000 1.0291 0.01187 0.00459 -0.0970 0.4265 0.5301 5.250 1.0559 0.01201 0.00476 -0.0970 0.4252 0.5325 5.500 1.0828 0.01210 0.00494 -0.0971 0.4239 0.5349 5.750 1.1095 0.01220 0.00513 -0.0971 0.4226 0.5373 6.000 1.1361 0.01231 0.00533 -0.0971 0.4212 0.5400 6.250 1.1626 0.01243 0.00553 -0.0971 0.4197 0.5429 6.500 1.1890 0.01256 0.00573 -0.0970 0.4183 0.5459 6.750 1.2151 0.01269 0.00594 -0.0970 0.4169 0.5490 7.000 1.2401 0.01277 0.00607 -0.0966 0.4132 0.5524 7.250 1.2635 0.01276 0.00616 -0.0960 0.4035 0.5562 7.500 1.2858 0.01283 0.00625 -0.0952 0.3917 0.5604 7.750 1.3074 0.01299 0.00643 -0.0943 0.3806 0.5646 8.000 1.3280 0.01322 0.00669 -0.0933 0.3657 0.5696 8.250 1.3392 0.01380 0.00711 -0.0907 0.3226 0.5748 8.500 1.3110 0.01592 0.00869 -0.0819 0.2334 0.5782 8.750 1.2866 0.01792 0.01042 -0.0743 0.1786 0.5825 9.000 1.2513 0.02063 0.01288 -0.0664 0.1241 0.5870 9.500 1.2065 0.02690 0.01903 -0.0589 0.0655 0.5986 9.750 1.1741 0.03204 0.02408 -0.0568 0.0307 0.6041 10.000 1.1570 0.03602 0.02808 -0.0555 0.0134 0.6125 10.250 1.1506 0.03906 0.03119 -0.0546 0.0085 0.6226 10.500 1.1498 0.04157 0.03382 -0.0540 0.0073 0.6381 10.750 1.1472 0.04426 0.03666 -0.0533 0.0060 0.6579 11.000 1.1461 0.04678 0.03935 -0.0527 0.0055 0.6920 11.500 1.1614 0.05206 0.04535 -0.0554 0.0044 1.0000 11.750 1.1620 0.05479 0.04815 -0.0552 0.0043 1.0000 12.000 1.1650 0.05732 0.05072 -0.0551 0.0038 1.0000 12.250 1.1660 0.06012 0.05358 -0.0550 0.0038 1.0000 12.500 1.1657 0.06311 0.05664 -0.0550 0.0035 1.0000 12.750 1.1651 0.06621 0.05981 -0.0550 0.0033 1.0000 13.000 1.1677 0.06897 0.06264 -0.0551 0.0032 1.0000 13.250 1.1704 0.07174 0.06547 -0.0552 0.0031 1.0000 13.500 1.1725 0.07464 0.06844 -0.0554 0.0029 1.0000 13.750 1.1744 0.07760 0.07148 -0.0556 0.0029 1.0000 14.000 1.1761 0.08062 0.07457 -0.0559 0.0028 1.0000 14.250 1.1776 0.08367 0.07768 -0.0563 0.0027 1.0000 14.500 1.1799 0.08667 0.08076 -0.0567 0.0028 1.0000 14.750 1.1816 0.08980 0.08395 -0.0571 0.0026 1.0000