XFOIL Version 6.96 Calculated polar for: GOE 493 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 ------ -------- --------- --------- -------- -------- -------- -17.000 -0.6573 0.11018 0.10726 -0.0638 1.0000 0.0171 -16.750 -0.7004 0.09796 0.09485 -0.0704 1.0000 0.0168 -16.500 -0.7283 0.08921 0.08594 -0.0752 1.0000 0.0167 -16.250 -0.7502 0.08197 0.07857 -0.0791 1.0000 0.0167 -16.000 -0.7685 0.07566 0.07213 -0.0825 1.0000 0.0167 -15.750 -0.7859 0.06983 0.06618 -0.0855 1.0000 0.0168 -15.500 -0.8017 0.06467 0.06090 -0.0879 1.0000 0.0169 -15.250 -0.8153 0.06010 0.05621 -0.0899 1.0000 0.0169 -15.000 -0.8283 0.05589 0.05189 -0.0914 1.0000 0.0170 -14.750 -0.8412 0.05200 0.04789 -0.0925 1.0000 0.0171 -14.500 -0.8517 0.04870 0.04450 -0.0930 1.0000 0.0172 -14.250 -0.8650 0.04558 0.04127 -0.0929 1.0000 0.0174 -14.000 -0.8789 0.04303 0.03864 -0.0917 1.0000 0.0174 -13.750 -0.8972 0.04076 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0.2476 -4.250 -0.0299 0.00916 0.00328 -0.1053 0.8349 0.2757 -4.000 -0.0028 0.00893 0.00312 -0.1053 0.8301 0.3082 -3.750 0.0203 0.00874 0.00303 -0.1044 0.8235 0.3385 -3.500 0.0463 0.00858 0.00292 -0.1040 0.8178 0.3672 -3.250 0.0728 0.00845 0.00283 -0.1037 0.8123 0.3942 -3.000 0.0976 0.00834 0.00278 -0.1031 0.8055 0.4187 -2.750 0.1252 0.00826 0.00269 -0.1030 0.7999 0.4407 -2.500 0.1505 0.00820 0.00266 -0.1024 0.7933 0.4591 -2.250 0.1767 0.00813 0.00260 -0.1021 0.7868 0.4768 -2.000 0.2038 0.00809 0.00256 -0.1019 0.7807 0.4941 -1.750 0.2291 0.00804 0.00253 -0.1013 0.7732 0.5098 -1.500 0.2572 0.00803 0.00247 -0.1013 0.7671 0.5245 -1.000 0.3088 0.00797 0.00243 -0.1003 0.7517 0.5542 -0.750 0.3331 0.00793 0.00243 -0.0995 0.7426 0.5694 -0.500 0.3596 0.00791 0.00240 -0.0991 0.7348 0.5858 -0.250 0.3841 0.00788 0.00241 -0.0984 0.7257 0.6007 0.000 0.4098 0.00787 0.00239 -0.0979 0.7174 0.6153 0.250 0.4345 0.00785 0.00240 -0.0972 0.7081 0.6305 0.500 0.4595 0.00784 0.00241 -0.0965 0.6995 0.6469 0.750 0.4844 0.00783 0.00244 -0.0959 0.6913 0.6655 1.000 0.5091 0.00783 0.00249 -0.0952 0.6836 0.6866 1.250 0.5335 0.00783 0.00254 -0.0944 0.6754 0.7096 1.500 0.5576 0.00783 0.00261 -0.0936 0.6677 0.7337 1.750 0.5817 0.00785 0.00267 -0.0927 0.6598 0.7589 2.000 0.6056 0.00785 0.00275 -0.0918 0.6526 0.7847 2.250 0.6291 0.00786 0.00283 -0.0908 0.6449 0.8116 2.500 0.6528 0.00787 0.00291 -0.0898 0.6379 0.8403 2.750 0.6769 0.00786 0.00300 -0.0889 0.6302 0.8731 3.000 0.7086 0.00790 0.00312 -0.0896 0.6229 0.9112 3.250 0.7569 0.00801 0.00329 -0.0941 0.6141 0.9447 3.500 0.8054 0.00817 0.00344 -0.0988 0.6057 0.9680 3.750 0.8484 0.00833 0.00356 -0.1022 0.5940 0.9847 4.000 0.8886 0.00849 0.00371 -0.1051 0.5813 1.0000 4.250 0.9050 0.00860 0.00379 -0.1028 0.5695 1.0000 4.500 0.9215 0.00875 0.00388 -0.1005 0.5568 1.0000 4.750 0.9391 0.00891 0.00399 -0.0985 0.5459 1.0000 5.000 0.9572 0.00904 0.00412 -0.0965 0.5344 1.0000 5.250 0.9743 0.00920 0.00426 -0.0943 0.5216 1.0000 5.500 0.9895 0.00939 0.00440 -0.0918 0.5056 1.0000 5.750 1.0039 0.00960 0.00456 -0.0891 0.4882 1.0000 6.000 1.0172 0.00983 0.00474 -0.0862 0.4712 1.0000 6.250 1.0271 0.01010 0.00494 -0.0826 0.4517 1.0000 6.500 1.0379 0.01040 0.00516 -0.0793 0.4291 1.0000 6.750 1.0468 0.01081 0.00545 -0.0757 0.4039 1.0000 7.000 1.0569 0.01125 0.00579 -0.0725 0.3773 1.0000 7.250 1.0660 0.01179 0.00620 -0.0692 0.3511 1.0000 7.500 1.0748 0.01239 0.00667 -0.0660 0.3259 1.0000 7.750 1.0861 0.01295 0.00714 -0.0632 0.3017 1.0000 8.000 1.0954 0.01362 0.00768 -0.0603 0.2729 1.0000 8.250 1.0972 0.01466 0.00844 -0.0564 0.2183 1.0000 8.500 1.0875 0.01637 0.00970 -0.0510 0.1478 1.0000 9.000 1.0853 0.01926 0.01208 -0.0435 0.0648 1.0000 9.250 1.0933 0.02031 0.01306 -0.0411 0.0532 1.0000 9.500 1.1035 0.02126 0.01401 -0.0391 0.0482 1.0000 9.750 1.1154 0.02214 0.01492 -0.0373 0.0454 1.0000 10.000 1.1248 0.02320 0.01599 -0.0354 0.0429 1.0000 10.250 1.1328 0.02438 0.01720 -0.0334 0.0410 1.0000 10.500 1.1446 0.02535 0.01823 -0.0319 0.0397 1.0000 10.750 1.1546 0.02646 0.01941 -0.0304 0.0384 1.0000 11.000 1.1632 0.02770 0.02070 -0.0288 0.0373 1.0000 11.250 1.1699 0.02913 0.02216 -0.0271 0.0362 1.0000 11.500 1.1705 0.03104 0.02412 -0.0251 0.0348 1.0000 11.750 1.1765 0.03263 0.02577 -0.0236 0.0340 1.0000 12.000 1.1854 0.03403 0.02725 -0.0224 0.0334 1.0000 12.250 1.1933 0.03554 0.02884 -0.0213 0.0326 1.0000 12.500 1.2001 0.03720 0.03055 -0.0201 0.0317 1.0000 12.750 1.2066 0.03891 0.03231 -0.0191 0.0308 1.0000 13.000 1.2116 0.04078 0.03422 -0.0181 0.0299 1.0000 13.250 1.2124 0.04307 0.03655 -0.0169 0.0292 1.0000 13.500 1.2117 0.04548 0.03901 -0.0155 0.0284 1.0000 13.750 1.2206 0.04714 0.04076 -0.0149 0.0279 1.0000 14.000 1.2283 0.04893 0.04263 -0.0143 0.0273 1.0000 14.250 1.2350 0.05083 0.04461 -0.0137 0.0266 1.0000 14.500 1.2413 0.05281 0.04665 -0.0132 0.0259 1.0000 14.750 1.2474 0.05483 0.04871 -0.0127 0.0252 1.0000 15.000 1.2526 0.05694 0.05085 -0.0123 0.0246 1.0000 15.250 1.2563 0.05905 0.05297 -0.0115 0.0239 1.0000 15.500 1.2612 0.06106 0.05504 -0.0105 0.0233 1.0000 15.750 1.2666 0.06335 0.05746 -0.0105 0.0228 1.0000 16.000 1.2718 0.06562 0.05983 -0.0103 0.0223 1.0000 16.250 1.2767 0.06794 0.06223 -0.0102 0.0218 1.0000 16.500 1.2808 0.07035 0.06473 -0.0102 0.0213 1.0000 16.750 1.2842 0.07296 0.06739 -0.0104 0.0207 1.0000 17.000 1.2878 0.07549 0.06997 -0.0106 0.0203 1.0000 17.250 1.2913 0.07802 0.07253 -0.0107 0.0198 1.0000 17.500 1.2967 0.07983 0.07437 -0.0096 0.0192 1.0000 17.750 1.2953 0.08332 0.07801 -0.0106 0.0189 1.0000 18.000 1.2955 0.08650 0.08132 -0.0111 0.0186 1.0000 18.250 1.2948 0.08987 0.08482 -0.0118 0.0183 1.0000 18.500 1.2939 0.09326 0.08833 -0.0125 0.0180 1.0000 18.750 1.2927 0.09674 0.09193 -0.0135 0.0176 1.0000 19.000 1.2906 0.10038 0.09568 -0.0145 0.0173 1.0000 19.250 1.2881 0.10418 0.09958 -0.0158 0.0170 1.0000