XFOIL Version 6.96 Calculated polar for: NACA 1412 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.9139 0.15280 0.15010 0.0146 1.0000 0.0153 -18.250 -0.9813 0.13333 0.13042 0.0039 1.0000 0.0153 -18.000 -1.0190 0.12143 0.11838 -0.0026 1.0000 0.0154 -17.750 -1.0557 0.11030 0.10710 -0.0086 1.0000 0.0154 -17.500 -1.0921 0.09963 0.09628 -0.0144 1.0000 0.0153 -17.250 -1.1284 0.08941 0.08592 -0.0200 1.0000 0.0153 -17.000 -1.1627 0.07982 0.07616 -0.0253 1.0000 0.0152 -16.750 -1.1930 0.07091 0.06708 -0.0304 1.0000 0.0152 -16.500 -1.2179 0.06292 0.05892 -0.0352 1.0000 0.0152 -16.250 -1.2364 0.05602 0.05187 -0.0396 1.0000 0.0153 -16.000 -1.2488 0.05029 0.04599 -0.0433 1.0000 0.0155 -15.750 -1.2563 0.04559 0.04115 -0.0462 1.0000 0.0157 -15.500 -1.2597 0.04178 0.03721 -0.0483 1.0000 0.0160 -15.250 -1.2603 0.03865 0.03395 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0.9683 0.0546 -5.750 -0.5066 0.01128 0.00448 -0.0301 0.9625 0.0618 -5.500 -0.4752 0.01097 0.00421 -0.0310 0.9577 0.0706 -5.250 -0.4473 0.01070 0.00396 -0.0310 0.9498 0.0797 -5.000 -0.4169 0.01043 0.00372 -0.0315 0.9435 0.0900 -4.500 -0.3612 0.00993 0.00329 -0.0314 0.9256 0.1141 -4.250 -0.3339 0.00969 0.00310 -0.0312 0.9152 0.1295 -4.000 -0.3068 0.00945 0.00291 -0.0310 0.9043 0.1470 -3.750 -0.2797 0.00923 0.00273 -0.0308 0.8929 0.1652 -3.500 -0.2528 0.00903 0.00257 -0.0305 0.8804 0.1841 -3.250 -0.2259 0.00884 0.00242 -0.0302 0.8668 0.2057 -3.000 -0.1995 0.00860 0.00228 -0.0298 0.8527 0.2384 -2.750 -0.1732 0.00838 0.00216 -0.0295 0.8377 0.2738 -2.500 -0.1465 0.00822 0.00204 -0.0292 0.8221 0.3022 -2.250 -0.1197 0.00807 0.00194 -0.0288 0.8058 0.3298 -2.000 -0.0929 0.00795 0.00185 -0.0285 0.7889 0.3560 -1.250 -0.0131 0.00762 0.00165 -0.0275 0.7346 0.4529 -1.000 0.0132 0.00750 0.00160 -0.0271 0.7151 0.4933 -0.750 0.0396 0.00742 0.00157 -0.0267 0.6948 0.5303 -0.500 0.0661 0.00736 0.00156 -0.0263 0.6744 0.5645 -0.250 0.0925 0.00732 0.00155 -0.0259 0.6547 0.5981 0.250 0.1454 0.00725 0.00157 -0.0251 0.6167 0.6649 0.500 0.1718 0.00722 0.00160 -0.0247 0.5977 0.6987 0.750 0.1980 0.00721 0.00164 -0.0242 0.5786 0.7309 1.500 0.2760 0.00731 0.00182 -0.0225 0.5176 0.8211 1.750 0.3021 0.00737 0.00190 -0.0219 0.4991 0.8482 2.000 0.3282 0.00745 0.00199 -0.0213 0.4810 0.8738 2.250 0.3546 0.00756 0.00210 -0.0208 0.4625 0.8967 2.500 0.3818 0.00772 0.00220 -0.0204 0.4414 0.9170 2.750 0.4103 0.00790 0.00232 -0.0204 0.4155 0.9346 3.250 0.4715 0.00830 0.00257 -0.0214 0.3709 0.9609 3.500 0.5024 0.00856 0.00271 -0.0221 0.3422 0.9708 3.750 0.5358 0.00886 0.00287 -0.0234 0.3103 0.9776 4.000 0.5673 0.00922 0.00306 -0.0244 0.2714 0.9844 4.250 0.6011 0.00964 0.00327 -0.0259 0.2314 0.9889 4.500 0.6336 0.01000 0.00349 -0.0271 0.2013 0.9936 4.750 0.6679 0.01034 0.00371 -0.0288 0.1758 0.9968 5.000 0.7013 0.01068 0.00396 -0.0302 0.1537 1.0000 5.250 0.7231 0.01098 0.00417 -0.0291 0.1366 1.0000 5.500 0.7449 0.01128 0.00440 -0.0280 0.1206 1.0000 5.750 0.7667 0.01161 0.00465 -0.0269 0.1055 1.0000 6.000 0.7885 0.01195 0.00492 -0.0258 0.0918 1.0000 6.250 0.8104 0.01229 0.00521 -0.0247 0.0801 1.0000 6.500 0.8325 0.01263 0.00550 -0.0237 0.0704 1.0000 6.750 0.8547 0.01299 0.00582 -0.0227 0.0616 1.0000 7.000 0.8770 0.01337 0.00616 -0.0217 0.0542 1.0000 7.250 0.8999 0.01372 0.00650 -0.0208 0.0493 1.0000 7.500 0.9225 0.01412 0.00688 -0.0200 0.0455 1.0000 7.750 0.9456 0.01447 0.00725 -0.0192 0.0430 1.0000 8.000 0.9683 0.01487 0.00765 -0.0183 0.0407 1.0000 8.250 0.9904 0.01534 0.00812 -0.0174 0.0387 1.0000 8.500 1.0132 0.01573 0.00856 -0.0166 0.0376 1.0000 8.750 1.0358 0.01615 0.00901 -0.0158 0.0366 1.0000 9.000 1.0580 0.01658 0.00949 -0.0150 0.0355 1.0000 9.250 1.0798 0.01705 0.00999 -0.0141 0.0344 1.0000 9.500 1.1007 0.01758 0.01054 -0.0131 0.0334 1.0000 9.750 1.1200 0.01823 0.01121 -0.0120 0.0323 1.0000 10.000 1.1405 0.01876 0.01180 -0.0109 0.0316 1.0000 10.250 1.1610 0.01926 0.01236 -0.0099 0.0309 1.0000 10.500 1.1808 0.01979 0.01296 -0.0088 0.0301 1.0000 10.750 1.1999 0.02036 0.01357 -0.0077 0.0293 1.0000 11.000 1.2181 0.02095 0.01422 -0.0065 0.0286 1.0000 11.250 1.2348 0.02162 0.01493 -0.0050 0.0278 1.0000 11.500 1.2474 0.02240 0.01575 -0.0030 0.0271 1.0000 11.750 1.2588 0.02325 0.01665 -0.0009 0.0265 1.0000 12.000 1.2736 0.02391 0.01740 0.0007 0.0260 1.0000 12.250 1.2873 0.02467 0.01825 0.0023 0.0254 1.0000 12.500 1.3002 0.02551 0.01917 0.0038 0.0248 1.0000 12.750 1.3125 0.02641 0.02014 0.0053 0.0242 1.0000 13.000 1.3245 0.02737 0.02117 0.0067 0.0236 1.0000 13.250 1.3352 0.02845 0.02231 0.0080 0.0230 1.0000 13.500 1.3435 0.02978 0.02370 0.0092 0.0224 1.0000 13.750 1.3481 0.03148 0.02546 0.0105 0.0219 1.0000 14.000 1.3576 0.03287 0.02697 0.0113 0.0216 1.0000 14.250 1.3658 0.03442 0.02864 0.0120 0.0211 1.0000 14.500 1.3730 0.03616 0.03049 0.0125 0.0206 1.0000 14.750 1.3794 0.03805 0.03248 0.0128 0.0201 1.0000 15.000 1.3849 0.04012 0.03465 0.0129 0.0196 1.0000 15.250 1.3896 0.04238 0.03700 0.0128 0.0191 1.0000 15.500 1.3924 0.04495 0.03965 0.0124 0.0187 1.0000 15.750 1.3925 0.04793 0.04272 0.0118 0.0183 1.0000 16.000 1.3893 0.05145 0.04635 0.0108 0.0180 1.0000 16.250 1.3865 0.05500 0.05002 0.0098 0.0177 1.0000 16.500 1.3823 0.05884 0.05400 0.0085 0.0174 1.0000 16.750 1.3767 0.06300 0.05829 0.0070 0.0171 1.0000 17.000 1.3690 0.06754 0.06296 0.0052 0.0168 1.0000 17.250 1.3600 0.07241 0.06796 0.0032 0.0166 1.0000 17.500 1.3493 0.07765 0.07333 0.0009 0.0163 1.0000 17.750 1.3371 0.08324 0.07905 -0.0016 0.0161 1.0000 18.000 1.3235 0.08918 0.08511 -0.0043 0.0159 1.0000 18.250 1.3086 0.09547 0.09152 -0.0073 0.0157 1.0000 18.500 1.2923 0.10210 0.09828 -0.0105 0.0156 1.0000 18.750 1.2755 0.10895 0.10524 -0.0139 0.0154 1.0000 19.000 1.2577 0.11614 0.11255 -0.0175 0.0153 1.0000 19.250 1.2398 0.12345 0.11997 -0.0214 0.0151 1.0000