XFOIL Version 6.96 Calculated polar for: AH 93-W-257 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.500 -0.9749 0.09562 0.08945 -0.0295 1.0000 0.1231 -17.250 -0.9722 0.09282 0.08669 -0.0305 1.0000 0.1269 -17.000 -0.9715 0.08972 0.08359 -0.0316 1.0000 0.1316 -16.750 -0.9698 0.08680 0.08067 -0.0326 1.0000 0.1364 -16.500 -0.9699 0.08370 0.07760 -0.0336 1.0000 0.1418 -16.250 -0.9691 0.08068 0.07457 -0.0345 1.0000 0.1475 -16.000 -0.9695 0.07761 0.07154 -0.0355 1.0000 0.1536 -15.750 -0.9693 0.07458 0.06850 -0.0364 1.0000 0.1602 -15.500 -0.9699 0.07156 0.06553 -0.0373 1.0000 0.1673 -15.250 -0.9701 0.06855 0.06253 -0.0382 1.0000 0.1746 -15.000 -0.9700 0.06565 0.05966 -0.0390 1.0000 0.1826 -14.750 -0.9697 0.06282 0.05685 -0.0398 1.0000 0.1901 -14.500 -0.9686 0.06007 0.05410 -0.0406 1.0000 0.1982 -14.250 -0.9604 0.05751 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0.4959 0.000 0.3072 0.01830 0.00977 -0.0890 0.5336 0.4986 0.250 0.3381 0.01842 0.00987 -0.0897 0.5315 0.5018 0.500 0.3693 0.01846 0.00996 -0.0906 0.5290 0.5052 0.750 0.4019 0.01844 0.00994 -0.0919 0.5264 0.5093 1.000 0.4338 0.01846 0.00997 -0.0930 0.5239 0.5129 1.250 0.4629 0.01863 0.01022 -0.0932 0.5215 0.5151 1.500 0.4925 0.01878 0.01041 -0.0935 0.5192 0.5175 1.750 0.5227 0.01888 0.01055 -0.0940 0.5169 0.5202 2.000 0.5536 0.01894 0.01060 -0.0947 0.5147 0.5233 2.250 0.5856 0.01898 0.01060 -0.0957 0.5126 0.5269 2.500 0.6196 0.01900 0.01052 -0.0972 0.5107 0.5313 2.750 0.6477 0.01919 0.01085 -0.0973 0.5084 0.5334 3.000 0.6761 0.01939 0.01117 -0.0975 0.5058 0.5355 3.250 0.7049 0.01957 0.01142 -0.0977 0.5029 0.5377 3.500 0.7343 0.01970 0.01161 -0.0981 0.5002 0.5402 3.750 0.7644 0.01982 0.01177 -0.0986 0.4978 0.5432 4.000 0.7954 0.01991 0.01186 -0.0994 0.4956 0.5469 4.250 0.8281 0.01993 0.01182 -0.1006 0.4935 0.5510 4.500 0.8581 0.02004 0.01195 -0.1010 0.4914 0.5531 4.750 0.8857 0.02027 0.01228 -0.1010 0.4888 0.5549 5.000 0.9128 0.02053 0.01268 -0.1010 0.4860 0.5570 5.250 0.9403 0.02076 0.01301 -0.1011 0.4829 0.5594 5.500 0.9686 0.02093 0.01325 -0.1013 0.4799 0.5622 5.750 0.9980 0.02105 0.01341 -0.1017 0.4773 0.5653 6.000 1.0285 0.02112 0.01348 -0.1024 0.4748 0.5685 6.250 1.0607 0.02116 0.01345 -0.1034 0.4724 0.5720 6.500 1.0875 0.02139 0.01378 -0.1033 0.4696 0.5739 6.750 1.1119 0.02170 0.01426 -0.1028 0.4658 0.5758 7.000 1.1374 0.02194 0.01462 -0.1025 0.4621 0.5778 7.250 1.1642 0.02209 0.01485 -0.1024 0.4585 0.5800 7.500 1.1923 0.02215 0.01493 -0.1025 0.4551 0.5824 7.750 1.2214 0.02220 0.01497 -0.1027 0.4516 0.5853 8.000 1.2438 0.02252 0.01544 -0.1022 0.4460 0.5884 8.250 1.2696 0.02267 0.01565 -0.1022 0.4408 0.5918 8.500 1.2965 0.02269 0.01567 -0.1021 0.4360 0.5941 8.750 1.3191 0.02289 0.01595 -0.1013 0.4305 0.5958 9.000 1.3381 0.02322 0.01642 -0.1001 0.4235 0.5976 9.250 1.3606 0.02334 0.01656 -0.0992 0.4173 0.5997 9.500 1.3781 0.02372 0.01706 -0.0978 0.4101 0.6021 9.750 1.3944 0.02407 0.01747 -0.0962 0.4020 0.6047 10.000 1.4087 0.02446 0.01789 -0.0944 0.3939 0.6073 10.250 1.4130 0.02505 0.01855 -0.0913 0.3848 0.6098 10.500 1.4222 0.02583 0.01933 -0.0893 0.3751 0.6124 10.750 1.4292 0.02690 0.02040 -0.0876 0.3640 0.6149 11.000 1.4319 0.02838 0.02197 -0.0858 0.3525 0.6166 11.250 1.4328 0.03018 0.02380 -0.0842 0.3405 0.6184 11.500 1.4304 0.03242 0.02604 -0.0829 0.3274 0.6202 11.750 1.4258 0.03506 0.02873 -0.0818 0.3131 0.6220 12.000 1.4192 0.03800 0.03166 -0.0808 0.2985 0.6238 12.250 1.4099 0.04124 0.03489 -0.0799 0.2835 0.6256 12.500 1.3986 0.04475 0.03837 -0.0790 0.2686 0.6274 12.750 1.3863 0.04840 0.04198 -0.0782 0.2538 0.6292 13.000 1.3736 0.05215 0.04568 -0.0775 0.2394 0.6309 13.250 1.3618 0.05599 0.04946 -0.0770 0.2252 0.6328 13.500 1.3510 0.05991 0.05333 -0.0767 0.2115 0.6348 13.750 1.3419 0.06376 0.05713 -0.0766 0.1982 0.6366 14.000 1.3343 0.06744 0.06080 -0.0764 0.1856 0.6380 14.250 1.3269 0.07119 0.06455 -0.0763 0.1739 0.6394 14.500 1.3204 0.07489 0.06823 -0.0762 0.1629 0.6408 14.750 1.3141 0.07865 0.07199 -0.0763 0.1527 0.6423 15.000 1.3088 0.08237 0.07569 -0.0765 0.1426 0.6438 15.250 1.3058 0.08588 0.07920 -0.0767 0.1332 0.6454 15.500 1.3027 0.08941 0.08273 -0.0770 0.1246 0.6471 15.750 1.2992 0.09308 0.08639 -0.0774 0.1167 0.6488 16.000 1.2969 0.09662 0.08992 -0.0779 0.1092 0.6506