XFOIL Version 6.96 Calculated polar for: N-12 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -1.0807 0.11303 0.11069 -0.0093 1.0000 0.0060 -18.250 -1.1361 0.09825 0.09571 -0.0171 1.0000 0.0058 -18.000 -1.1754 0.08706 0.08436 -0.0232 1.0000 0.0058 -17.750 -1.2157 0.07623 0.07334 -0.0293 1.0000 0.0057 -17.500 -1.2430 0.06798 0.06492 -0.0339 1.0000 0.0056 -17.250 -1.2665 0.06047 0.05725 -0.0382 1.0000 0.0056 -17.000 -1.2845 0.05408 0.05070 -0.0418 1.0000 0.0056 -16.750 -1.2969 0.04902 0.04551 -0.0443 1.0000 0.0057 -16.500 -1.3079 0.04458 0.04093 -0.0461 1.0000 0.0057 -16.250 -1.3158 0.04093 0.03716 -0.0470 1.0000 0.0058 -16.000 -1.3188 0.03813 0.03426 -0.0471 1.0000 0.0060 -15.750 -1.3213 0.03561 0.03163 -0.0468 1.0000 0.0061 -15.500 -1.3239 0.03328 0.02919 -0.0459 1.0000 0.0062 -15.250 -1.3233 0.03142 0.02722 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-0.6315 0.01139 0.00554 0.0007 0.9773 0.0232 -5.500 -0.6065 0.01085 0.00496 0.0012 0.9718 0.0239 -5.000 -0.5570 0.01009 0.00414 0.0024 0.9517 0.0248 -4.750 -0.5200 0.00971 0.00374 0.0003 0.9404 0.0254 -4.500 -0.4739 0.00937 0.00338 -0.0039 0.9322 0.0263 -4.250 -0.4217 0.00907 0.00307 -0.0095 0.9245 0.0271 -4.000 -0.3692 0.00880 0.00274 -0.0152 0.9103 0.0280 -3.750 -0.3288 0.00868 0.00249 -0.0180 0.8794 0.0286 -3.500 -0.3028 0.00863 0.00233 -0.0176 0.8516 0.0289 -3.250 -0.2791 0.00858 0.00218 -0.0166 0.8245 0.0293 -3.000 -0.2555 0.00853 0.00205 -0.0156 0.8017 0.0297 -2.750 -0.2318 0.00848 0.00192 -0.0146 0.7793 0.0301 -2.500 -0.2090 0.00847 0.00180 -0.0134 0.7483 0.0304 -2.250 -0.1869 0.00851 0.00169 -0.0121 0.7076 0.0307 -2.000 -0.1659 0.00861 0.00159 -0.0105 0.6515 0.0321 -1.750 -0.1433 0.00868 0.00151 -0.0094 0.6088 0.0341 -1.500 -0.1193 0.00867 0.00144 -0.0085 0.5823 0.0386 -1.250 -0.0976 0.00845 0.00133 -0.0073 0.5563 0.0991 -1.000 -0.0737 0.00844 0.00128 -0.0065 0.5289 0.1115 -0.750 -0.0497 0.00842 0.00124 -0.0056 0.5009 0.1268 -0.500 -0.0273 0.00833 0.00118 -0.0045 0.4692 0.1648 -0.250 -0.0124 0.00773 0.00106 -0.0021 0.4355 0.3333 0.000 0.0070 0.00795 0.00109 -0.0005 0.3482 0.3709 0.250 0.0296 0.00805 0.00112 0.0005 0.3046 0.3950 0.500 0.0525 0.00803 0.00112 0.0015 0.2797 0.4293 0.750 0.0749 0.00792 0.00112 0.0026 0.2627 0.4764 1.000 0.0955 0.00771 0.00112 0.0041 0.2478 0.5523 1.250 0.1152 0.00750 0.00115 0.0058 0.2353 0.6343 1.500 0.1361 0.00736 0.00118 0.0074 0.2265 0.6947 1.750 0.1582 0.00731 0.00123 0.0087 0.2163 0.7323 2.000 0.1815 0.00734 0.00130 0.0097 0.2015 0.7567 2.250 0.2019 0.00755 0.00140 0.0113 0.1423 0.7855 2.500 0.2225 0.00771 0.00156 0.0129 0.1124 0.8186 2.750 0.2463 0.00779 0.00167 0.0139 0.1045 0.8414 3.000 0.2715 0.00785 0.00177 0.0145 0.0999 0.8563 3.250 0.2969 0.00796 0.00188 0.0151 0.0934 0.8676 3.500 0.3226 0.00806 0.00199 0.0156 0.0807 0.8802 3.750 0.3468 0.00839 0.00217 0.0162 0.0417 0.8935 4.000 0.3808 0.00853 0.00237 0.0148 0.0365 0.9140 4.250 0.4220 0.00871 0.00259 0.0118 0.0342 0.9267 4.500 0.4622 0.00892 0.00282 0.0089 0.0332 0.9346 4.750 0.5041 0.00914 0.00306 0.0057 0.0321 0.9392 5.000 0.5441 0.00939 0.00332 0.0029 0.0308 0.9451 5.250 0.5792 0.00966 0.00359 0.0011 0.0297 0.9509 5.500 0.6113 0.00994 0.00389 0.0001 0.0286 0.9562 6.000 0.6661 0.01061 0.00462 0.0002 0.0262 0.9699 6.250 0.6925 0.01084 0.00486 0.0004 0.0259 0.9757 6.500 0.7227 0.01107 0.00511 -0.0002 0.0254 0.9791 6.750 0.7489 0.01133 0.00539 0.0000 0.0248 0.9841 7.000 0.7811 0.01159 0.00567 -0.0011 0.0238 0.9865 7.250 0.8126 0.01185 0.00595 -0.0021 0.0228 0.9885 7.500 0.8428 0.01212 0.00622 -0.0028 0.0217 0.9908 7.750 0.8713 0.01244 0.00655 -0.0032 0.0207 0.9929 8.000 0.8992 0.01285 0.00699 -0.0035 0.0196 0.9947 8.250 0.9303 0.01307 0.00723 -0.0044 0.0190 0.9960 8.500 0.9618 0.01333 0.00753 -0.0055 0.0180 0.9975 8.750 0.9940 0.01359 0.00779 -0.0067 0.0166 0.9990 9.000 1.0248 0.01390 0.00807 -0.0077 0.0153 1.0000 9.250 1.0435 0.01424 0.00844 -0.0060 0.0145 1.0000 9.500 1.0625 0.01457 0.00881 -0.0044 0.0137 1.0000 9.750 1.0813 0.01492 0.00919 -0.0028 0.0130 1.0000 10.000 1.0999 0.01528 0.00955 -0.0012 0.0119 1.0000 10.250 1.1175 0.01572 0.01000 0.0006 0.0109 1.0000 10.500 1.1352 0.01614 0.01047 0.0024 0.0105 1.0000 10.750 1.1523 0.01659 0.01098 0.0043 0.0101 1.0000 11.000 1.1692 0.01705 0.01148 0.0061 0.0096 1.0000 11.250 1.1853 0.01754 0.01202 0.0081 0.0091 1.0000 11.500 1.2007 0.01808 0.01260 0.0101 0.0088 1.0000 11.750 1.2148 0.01868 0.01325 0.0123 0.0083 1.0000 12.000 1.2285 0.01928 0.01392 0.0146 0.0080 1.0000 12.250 1.2420 0.01987 0.01458 0.0169 0.0078 1.0000 12.500 1.2550 0.02048 0.01526 0.0192 0.0075 1.0000 12.750 1.2650 0.02111 0.01596 0.0220 0.0074 1.0000 13.000 1.2721 0.02171 0.01663 0.0253 0.0071 1.0000 13.250 1.2791 0.02238 0.01737 0.0285 0.0070 1.0000 13.500 1.2864 0.02313 0.01819 0.0314 0.0067 1.0000 13.750 1.2934 0.02396 0.01910 0.0341 0.0066 1.0000 14.000 1.2999 0.02489 0.02010 0.0366 0.0063 1.0000 14.250 1.3044 0.02603 0.02132 0.0390 0.0063 1.0000 14.500 1.3066 0.02741 0.02279 0.0412 0.0060 1.0000 14.750 1.3072 0.02903 0.02452 0.0432 0.0058 1.0000 15.000 1.3108 0.03053 0.02613 0.0446 0.0057 1.0000 15.250 1.3130 0.03230 0.02800 0.0457 0.0057 1.0000 15.500 1.3138 0.03433 0.03013 0.0465 0.0056 1.0000 15.750 1.3138 0.03662 0.03254 0.0468 0.0055 1.0000 16.000 1.3106 0.03947 0.03551 0.0466 0.0054 1.0000 16.250 1.3072 0.04258 0.03874 0.0459 0.0054 1.0000 16.500 1.2988 0.04661 0.04290 0.0444 0.0053 1.0000 16.750 1.2898 0.05103 0.04746 0.0424 0.0053 1.0000 17.000 1.2730 0.05691 0.05350 0.0393 0.0053 1.0000 17.250 1.2523 0.06375 0.06050 0.0355 0.0053 1.0000 17.500 1.2329 0.07066 0.06754 0.0317 0.0052 1.0000 17.750 1.1987 0.08031 0.07736 0.0263 0.0053 1.0000 18.000 1.1696 0.08914 0.08634 0.0216 0.0053 1.0000 18.250 1.1258 0.10080 0.09816 0.0153 0.0054 1.0000 18.500 1.0848 0.11244 0.10995 0.0091 0.0054 1.0000 18.750 1.0327 0.12709 0.12478 0.0016 0.0056 1.0000 19.000 0.9678 0.14559 0.14344 -0.0080 0.0057 1.0000