XFOIL Version 6.96 Calculated polar for: Falcon 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 ------ -------- --------- --------- -------- -------- -------- -17.000 -1.1009 0.07843 0.07562 -0.0311 1.0000 0.0116 -16.750 -1.1335 0.06886 0.06585 -0.0368 1.0000 0.0116 -16.500 -1.1541 0.06173 0.05858 -0.0409 1.0000 0.0116 -16.250 -1.1706 0.05568 0.05238 -0.0442 1.0000 0.0117 -16.000 -1.1830 0.05062 0.04718 -0.0467 1.0000 0.0117 -15.750 -1.1903 0.04659 0.04303 -0.0482 1.0000 0.0118 -15.500 -1.1957 0.04312 0.03944 -0.0491 1.0000 0.0119 -15.250 -1.1988 0.04019 0.03640 -0.0493 1.0000 0.0120 -15.000 -1.1990 0.03778 0.03390 -0.0491 1.0000 0.0121 -14.750 -1.1998 0.03550 0.03151 -0.0483 1.0000 0.0123 -14.500 -1.1985 0.03358 0.02949 -0.0471 1.0000 0.0124 -14.250 -1.1953 0.03195 0.02776 -0.0457 1.0000 0.0126 -14.000 -1.1928 0.03039 0.02609 -0.0438 1.0000 0.0127 -13.750 -1.1883 0.02908 0.02468 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0.750 0.1522 0.00615 0.00146 -0.0007 0.4899 0.8283 1.000 0.1781 0.00617 0.00149 -0.0001 0.4773 0.8456 1.250 0.2041 0.00620 0.00152 0.0004 0.4649 0.8629 1.500 0.2305 0.00625 0.00157 0.0009 0.4526 0.8805 1.750 0.2577 0.00631 0.00162 0.0011 0.4400 0.8984 2.000 0.2854 0.00636 0.00166 0.0012 0.4275 0.9123 2.250 0.3167 0.00643 0.00171 0.0005 0.4152 0.9222 2.500 0.3488 0.00652 0.00176 -0.0004 0.4037 0.9320 2.750 0.3816 0.00662 0.00182 -0.0016 0.3915 0.9421 3.000 0.4232 0.00674 0.00190 -0.0048 0.3784 0.9475 3.250 0.4642 0.00686 0.00199 -0.0078 0.3672 0.9532 3.500 0.5061 0.00701 0.00209 -0.0111 0.3548 0.9573 3.750 0.5487 0.00718 0.00221 -0.0146 0.3424 0.9602 4.000 0.5893 0.00736 0.00235 -0.0175 0.3311 0.9638 4.250 0.6263 0.00753 0.00249 -0.0196 0.3209 0.9683 4.500 0.6632 0.00773 0.00265 -0.0217 0.3101 0.9708 5.000 0.7307 0.00813 0.00296 -0.0244 0.2882 0.9775 5.250 0.7637 0.00833 0.00313 -0.0257 0.2781 0.9815 5.500 0.7947 0.00857 0.00332 -0.0265 0.2674 0.9868 5.750 0.8269 0.00877 0.00351 -0.0276 0.2575 0.9925 6.000 0.8604 0.00902 0.00371 -0.0290 0.2464 0.9954 6.250 0.8958 0.00924 0.00389 -0.0309 0.2337 0.9971 6.500 0.9303 0.00950 0.00407 -0.0326 0.2176 0.9987 6.750 0.9640 0.00978 0.00428 -0.0341 0.2014 0.9999 7.000 0.9851 0.01001 0.00445 -0.0330 0.1905 1.0000 7.250 1.0050 0.01020 0.00462 -0.0315 0.1819 1.0000 7.500 1.0255 0.01043 0.00482 -0.0302 0.1727 1.0000 8.000 1.0684 0.01094 0.00527 -0.0279 0.1556 1.0000 8.250 1.0899 0.01124 0.00553 -0.0268 0.1470 1.0000 8.500 1.1120 0.01151 0.00578 -0.0258 0.1394 1.0000 8.750 1.1341 0.01181 0.00606 -0.0248 0.1324 1.0000 9.000 1.1560 0.01212 0.00634 -0.0238 0.1246 1.0000 9.250 1.1779 0.01245 0.00665 -0.0229 0.1161 1.0000 9.500 1.1982 0.01289 0.00703 -0.0217 0.1031 1.0000 9.750 1.2144 0.01364 0.00760 -0.0199 0.0778 1.0000 10.000 1.2148 0.01552 0.00908 -0.0157 0.0257 1.0000 10.250 1.2309 0.01624 0.00979 -0.0138 0.0201 1.0000 10.500 1.2485 0.01682 0.01039 -0.0123 0.0179 1.0000 10.750 1.2646 0.01749 0.01110 -0.0105 0.0163 1.0000 11.000 1.2824 0.01800 0.01166 -0.0090 0.0155 1.0000 11.250 1.2987 0.01860 0.01230 -0.0073 0.0147 1.0000 11.500 1.3132 0.01929 0.01303 -0.0054 0.0140 1.0000 11.750 1.3215 0.02014 0.01394 -0.0024 0.0133 1.0000 12.000 1.3274 0.02090 0.01477 0.0010 0.0129 1.0000 12.250 1.3373 0.02155 0.01548 0.0035 0.0126 1.0000 12.500 1.3460 0.02234 0.01634 0.0060 0.0123 1.0000 12.750 1.3540 0.02326 0.01732 0.0083 0.0119 1.0000 13.000 1.3616 0.02430 0.01842 0.0103 0.0116 1.0000 13.250 1.3680 0.02551 0.01969 0.0122 0.0113 1.0000 13.500 1.3729 0.02694 0.02119 0.0139 0.0111 1.0000 13.750 1.3755 0.02867 0.02300 0.0154 0.0108 1.0000 14.000 1.3736 0.03096 0.02539 0.0166 0.0106 1.0000 14.250 1.3681 0.03386 0.02841 0.0174 0.0104 1.0000 14.500 1.3584 0.03752 0.03220 0.0175 0.0102 1.0000 14.750 1.3581 0.04039 0.03517 0.0173 0.0101 1.0000 15.000 1.3576 0.04342 0.03829 0.0168 0.0100 1.0000 15.250 1.3534 0.04700 0.04198 0.0160 0.0100 1.0000 15.500 1.3476 0.05087 0.04595 0.0150 0.0099 1.0000 15.750 1.3381 0.05532 0.05051 0.0138 0.0098 1.0000 16.000 1.3280 0.05987 0.05517 0.0125 0.0097 1.0000 16.250 1.3164 0.06477 0.06018 0.0110 0.0097 1.0000 16.500 1.3027 0.07008 0.06561 0.0092 0.0096 1.0000 16.750 1.2896 0.07540 0.07103 0.0074 0.0095 1.0000 17.000 1.2742 0.08120 0.07694 0.0053 0.0095 1.0000 17.250 1.2598 0.08690 0.08274 0.0032 0.0095 1.0000