XFOIL Version 6.96 Calculated polar for: USA 45 M AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.4807 0.09624 0.09454 -0.0228 1.0000 0.0141 -11.000 -0.8188 0.03430 0.03182 -0.0522 1.0000 0.0175 -10.750 -0.8068 0.03339 0.03084 -0.0503 1.0000 0.0176 -10.250 -0.7494 0.03348 0.03091 -0.0514 0.9959 0.0178 -10.000 -0.7186 0.03355 0.03097 -0.0524 0.9891 0.0179 -9.750 -0.6889 0.03280 0.03016 -0.0538 0.9828 0.0180 -9.500 -0.6606 0.03147 0.02872 -0.0554 0.9757 0.0182 -9.250 -0.6293 0.03043 0.02759 -0.0573 0.9682 0.0184 -9.000 -0.5990 0.02847 0.02545 -0.0595 0.9574 0.0188 -8.750 -0.5917 0.02149 0.01773 -0.0593 0.9370 0.0203 -8.500 -0.5687 0.01982 0.01576 -0.0591 0.9142 0.0209 -8.250 -0.5476 0.01875 0.01444 -0.0582 0.8872 0.0212 -8.000 -0.5264 0.01799 0.01345 -0.0570 0.8604 0.0214 -7.750 -0.5049 0.01735 0.01259 -0.0559 0.8332 0.0215 -7.500 -0.4843 0.01645 0.01144 -0.0546 0.8068 0.0217 -7.250 -0.4638 0.01546 0.01022 -0.0534 0.7795 0.0222 -7.000 -0.4409 0.01504 0.00965 -0.0525 0.7504 0.0224 -6.750 -0.4174 0.01461 0.00906 -0.0517 0.7249 0.0226 -6.500 -0.3935 0.01425 0.00855 -0.0509 0.6974 0.0228 -6.250 -0.3693 0.01392 0.00806 -0.0501 0.6694 0.0229 -6.000 -0.3450 0.01358 0.00757 -0.0494 0.6399 0.0231 -5.750 -0.3203 0.01326 0.00711 -0.0488 0.6149 0.0233 -5.500 -0.2955 0.01292 0.00664 -0.0481 0.5898 0.0235 -5.250 -0.2705 0.01263 0.00620 -0.0475 0.5646 0.0238 -5.000 -0.2456 0.01234 0.00578 -0.0469 0.5379 0.0240 -4.750 -0.2203 0.01207 0.00538 -0.0463 0.5138 0.0243 -4.500 -0.1949 0.01181 0.00501 -0.0458 0.4941 0.0246 -4.250 -0.1692 0.01160 0.00470 -0.0453 0.4772 0.0249 -4.000 -0.1433 0.01141 0.00443 -0.0448 0.4616 0.0254 -3.750 -0.1174 0.01119 0.00412 -0.0443 0.4485 0.0257 -3.500 -0.0914 0.01098 0.00384 -0.0439 0.4381 0.0260 -3.000 -0.0388 0.01062 0.00337 -0.0431 0.4214 0.0264 -2.500 0.0142 0.01034 0.00299 -0.0423 0.4064 0.0267 -2.250 0.0406 0.01019 0.00280 -0.0420 0.3994 0.0269 -2.000 0.0665 0.00994 0.00249 -0.0415 0.3943 0.0274 -1.750 0.0931 0.00978 0.00230 -0.0411 0.3889 0.0279 -1.500 0.1197 0.00967 0.00215 -0.0408 0.3830 0.0284 -1.250 0.1467 0.00958 0.00204 -0.0405 0.3778 0.0289 -1.000 0.1737 0.00950 0.00194 -0.0402 0.3724 0.0296 -0.750 0.2007 0.00945 0.00187 -0.0399 0.3673 0.0303 -0.500 0.2279 0.00941 0.00181 -0.0397 0.3633 0.0312 -0.250 0.2552 0.00936 0.00175 -0.0395 0.3588 0.0321 0.000 0.2823 0.00934 0.00170 -0.0392 0.3536 0.0328 0.250 0.3095 0.00932 0.00166 -0.0390 0.3491 0.0334 0.500 0.3367 0.00927 0.00161 -0.0388 0.3451 0.0356 0.750 0.3639 0.00925 0.00159 -0.0385 0.3409 0.0380 1.000 0.3910 0.00926 0.00159 -0.0383 0.3362 0.0410 1.250 0.4181 0.00924 0.00159 -0.0381 0.3322 0.0489 1.500 0.4453 0.00922 0.00160 -0.0379 0.3283 0.0630 1.750 0.4682 0.00869 0.00162 -0.0371 0.3240 0.2902 2.000 0.4864 0.00786 0.00165 -0.0355 0.3201 0.6015 2.250 0.5046 0.00735 0.00171 -0.0335 0.3168 0.7863 2.500 0.5259 0.00710 0.00182 -0.0317 0.3131 0.8992 2.750 0.5651 0.00717 0.00196 -0.0340 0.3078 0.9555 3.000 0.6115 0.00732 0.00208 -0.0380 0.3027 0.9752 3.250 0.6508 0.00745 0.00218 -0.0404 0.2976 0.9844 3.500 0.6872 0.00760 0.00226 -0.0423 0.2904 0.9870 3.750 0.7226 0.00771 0.00234 -0.0440 0.2837 0.9902 4.000 0.7554 0.00785 0.00243 -0.0451 0.2773 0.9931 4.250 0.7883 0.00796 0.00252 -0.0463 0.2731 0.9950 4.500 0.8208 0.00806 0.00261 -0.0473 0.2691 0.9966 4.750 0.8524 0.00818 0.00271 -0.0483 0.2643 0.9980 5.000 0.8837 0.00832 0.00282 -0.0491 0.2576 0.9993 5.250 0.9123 0.00849 0.00294 -0.0494 0.2481 1.0000 5.500 0.9350 0.00864 0.00307 -0.0484 0.2405 1.0000 5.750 0.9573 0.00884 0.00322 -0.0474 0.2313 1.0000 6.000 0.9797 0.00903 0.00338 -0.0464 0.2210 1.0000 6.250 1.0014 0.00928 0.00357 -0.0453 0.2083 1.0000 6.500 1.0228 0.00957 0.00379 -0.0441 0.1939 1.0000 6.750 1.0427 0.00998 0.00407 -0.0427 0.1746 1.0000 7.000 1.0629 0.01037 0.00438 -0.0414 0.1566 1.0000 7.250 1.0816 0.01088 0.00476 -0.0399 0.1355 1.0000 7.500 1.1004 0.01140 0.00516 -0.0384 0.1148 1.0000 7.750 1.1101 0.01259 0.00602 -0.0356 0.0610 1.0000 8.000 1.1210 0.01368 0.00694 -0.0329 0.0186 1.0000 8.250 1.1414 0.01404 0.00730 -0.0317 0.0161 1.0000 8.500 1.1614 0.01443 0.00770 -0.0304 0.0139 1.0000 8.750 1.1820 0.01476 0.00806 -0.0293 0.0132 1.0000 9.000 1.2020 0.01513 0.00846 -0.0281 0.0123 1.0000 9.250 1.2212 0.01554 0.00888 -0.0268 0.0114 1.0000 9.500 1.2393 0.01600 0.00937 -0.0253 0.0106 1.0000 9.750 1.2576 0.01644 0.00984 -0.0239 0.0102 1.0000 10.000 1.2758 0.01685 0.01029 -0.0225 0.0098 1.0000 10.250 1.2931 0.01729 0.01076 -0.0210 0.0092 1.0000 10.500 1.3094 0.01775 0.01126 -0.0193 0.0088 1.0000 10.750 1.3217 0.01827 0.01181 -0.0169 0.0084 1.0000 11.000 1.3322 0.01883 0.01240 -0.0143 0.0081 1.0000 11.250 1.3412 0.01951 0.01313 -0.0117 0.0077 1.0000 11.500 1.3518 0.02017 0.01385 -0.0095 0.0076 1.0000 11.750 1.3623 0.02087 0.01461 -0.0074 0.0074 1.0000 12.000 1.3724 0.02165 0.01544 -0.0055 0.0071 1.0000 12.250 1.3810 0.02258 0.01644 -0.0036 0.0070 1.0000 12.500 1.3883 0.02366 0.01759 -0.0019 0.0068 1.0000 12.750 1.3956 0.02486 0.01884 -0.0005 0.0067 1.0000 13.000 1.4023 0.02620 0.02025 0.0007 0.0064 1.0000 13.250 1.4077 0.02778 0.02190 0.0016 0.0062 1.0000 13.500 1.4110 0.02971 0.02391 0.0023 0.0062 1.0000 13.750 1.4128 0.03197 0.02625 0.0025 0.0059 1.0000 14.000 1.4128 0.03464 0.02900 0.0024 0.0057 1.0000 14.250 1.4093 0.03791 0.03239 0.0018 0.0058 1.0000 14.500 1.4010 0.04201 0.03661 0.0008 0.0056 1.0000 14.750 1.3961 0.04579 0.04048 -0.0003 0.0055 1.0000 15.000 1.3888 0.04998 0.04479 -0.0016 0.0055 1.0000 15.250 1.3743 0.05515 0.05009 -0.0032 0.0055 1.0000 15.500 1.3640 0.05973 0.05477 -0.0046 0.0054 1.0000 15.750 1.3516 0.06460 0.05974 -0.0060 0.0054 1.0000 16.000 1.3362 0.06991 0.06516 -0.0076 0.0054 1.0000 16.250 1.3211 0.07527 0.07062 -0.0092 0.0053 1.0000 16.500 1.3083 0.08037 0.07581 -0.0108 0.0053 1.0000 16.750 1.2931 0.08593 0.08148 -0.0126 0.0052 1.0000