XFOIL Version 6.96 Calculated polar for: EPPLER 1214 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.7145 0.09799 0.09093 -0.0300 1.0000 0.0526 -15.500 -0.7118 0.09504 0.08802 -0.0310 1.0000 0.0543 -15.250 -0.7122 0.09156 0.08455 -0.0324 1.0000 0.0568 -15.000 -0.7129 0.08812 0.08109 -0.0337 1.0000 0.0595 -14.750 -0.7136 0.08478 0.07778 -0.0350 1.0000 0.0619 -14.500 -0.7166 0.08110 0.07409 -0.0364 1.0000 0.0654 -14.250 -0.7211 0.07736 0.07038 -0.0378 1.0000 0.0687 -14.000 -0.7268 0.07351 0.06653 -0.0393 1.0000 0.0727 -13.750 -0.7349 0.06956 0.06260 -0.0408 1.0000 0.0764 -13.500 -0.7442 0.06553 0.05858 -0.0423 1.0000 0.0807 -13.250 -0.7552 0.06136 0.05440 -0.0438 1.0000 0.0853 -13.000 -0.7687 0.05696 0.05001 -0.0455 1.0000 0.0902 -12.750 -0.7812 0.05271 0.04572 -0.0470 1.0000 0.0950 -12.500 -0.7981 0.04805 0.04105 -0.0488 1.0000 0.0999 -12.250 -0.8128 0.04372 0.03666 -0.0504 1.0000 0.1052 -12.000 -0.8313 0.03931 0.03222 -0.0519 1.0000 0.1102 -11.750 -0.8465 0.03579 0.02864 -0.0524 1.0000 0.1164 -11.500 -0.8606 0.03307 0.02590 -0.0515 1.0000 0.1228 -11.250 -0.8719 0.03113 0.02396 -0.0493 1.0000 0.1299 -11.000 -0.8810 0.02971 0.02255 -0.0459 1.0000 0.1386 -10.750 -0.8881 0.02860 0.02147 -0.0420 1.0000 0.1476 -10.500 -0.8890 0.02764 0.02057 -0.0387 1.0000 0.1586 -10.250 -0.8862 0.02686 0.01985 -0.0356 1.0000 0.1698 -10.000 -0.8812 0.02623 0.01925 -0.0326 1.0000 0.1816 -9.750 -0.8676 0.02567 0.01873 -0.0312 0.9928 0.1954 -9.500 -0.8320 0.02517 0.01820 -0.0336 0.9585 0.2138 -9.250 -0.7927 0.02488 0.01780 -0.0364 0.9218 0.2310 -9.000 -0.7508 0.02473 0.01753 -0.0392 0.8894 0.2445 -8.500 -0.6872 0.02441 0.01681 -0.0407 0.8284 0.2635 -8.250 -0.6637 0.02421 0.01637 -0.0399 0.8026 0.2711 -8.000 -0.6388 0.02421 0.01627 -0.0390 0.7800 0.2774 -7.750 -0.6179 0.02392 0.01570 -0.0378 0.7598 0.2845 -7.500 -0.5937 0.02377 0.01545 -0.0369 0.7410 0.2897 -7.250 -0.5692 0.02367 0.01524 -0.0360 0.7238 0.2950 -7.000 -0.5467 0.02341 0.01474 -0.0350 0.7083 0.3012 -6.750 -0.5228 0.02314 0.01431 -0.0342 0.6932 0.3064 -6.500 -0.4970 0.02301 0.01413 -0.0336 0.6782 0.3109 -6.250 -0.4724 0.02281 0.01379 -0.0328 0.6650 0.3162 -6.000 -0.4493 0.02253 0.01324 -0.0319 0.6519 0.3221 -5.750 -0.4236 0.02232 0.01299 -0.0313 0.6390 0.3263 -5.250 -0.3729 0.02197 0.01244 -0.0301 0.6152 0.3359 -5.000 -0.3486 0.02174 0.01196 -0.0293 0.6049 0.3412 -4.750 -0.3226 0.02151 0.01170 -0.0288 0.5932 0.3452 -4.500 -0.2965 0.02136 0.01147 -0.0282 0.5835 0.3493 -4.250 -0.2708 0.02119 0.01122 -0.0277 0.5725 0.3541 -4.000 -0.2453 0.02101 0.01085 -0.0271 0.5635 0.3591 -3.750 -0.2195 0.02081 0.01057 -0.0266 0.5531 0.3635 -3.500 -0.1932 0.02068 0.01038 -0.0261 0.5446 0.3676 -3.250 -0.1670 0.02055 0.01023 -0.0257 0.5347 0.3724 -3.000 -0.1410 0.02042 0.00998 -0.0252 0.5263 0.3776 -2.750 -0.1148 0.02031 0.00972 -0.0247 0.5180 0.3826 -2.500 -0.0884 0.02018 0.00962 -0.0243 0.5093 0.3869 -2.250 -0.0621 0.02011 0.00946 -0.0238 0.5021 0.3921 -2.000 -0.0359 0.02003 0.00936 -0.0234 0.4933 0.3978 -1.750 -0.0096 0.01997 0.00917 -0.0229 0.4860 0.4034 -1.500 0.0169 0.01989 0.00910 -0.0225 0.4792 0.4082 -1.250 0.0431 0.01985 0.00907 -0.0221 0.4713 0.4141 -1.000 0.0694 0.01983 0.00893 -0.0216 0.4648 0.4210 -0.750 0.0957 0.01980 0.00891 -0.0212 0.4580 0.4270 -0.500 0.1218 0.01978 0.00892 -0.0207 0.4509 0.4332 -0.250 0.1482 0.01979 0.00885 -0.0203 0.4452 0.4406 0.000 0.1744 0.01980 0.00887 -0.0199 0.4391 0.4479 0.250 0.2001 0.01982 0.00894 -0.0194 0.4324 0.4558 0.500 0.2264 0.01986 0.00890 -0.0190 0.4267 0.4649 0.750 0.2524 0.01988 0.00895 -0.0185 0.4216 0.4730 1.000 0.2781 0.01996 0.00909 -0.0180 0.4154 0.4830 1.250 0.3038 0.02000 0.00917 -0.0175 0.4099 0.4933 1.500 0.3299 0.02006 0.00918 -0.0170 0.4053 0.5055 1.750 0.3552 0.02015 0.00938 -0.0165 0.3998 0.5179 2.000 0.3806 0.02026 0.00955 -0.0160 0.3943 0.5322 2.250 0.4062 0.02033 0.00967 -0.0155 0.3897 0.5482 2.500 0.4323 0.02041 0.00976 -0.0150 0.3857 0.5667 2.750 0.4569 0.02056 0.01006 -0.0144 0.3805 0.5876 3.000 0.4819 0.02068 0.01031 -0.0139 0.3754 0.6120 3.250 0.5068 0.02077 0.01049 -0.0132 0.3711 0.6401 3.500 0.5321 0.02085 0.01064 -0.0125 0.3676 0.6730 3.750 0.5557 0.02102 0.01101 -0.0116 0.3633 0.7123 4.000 0.5804 0.02118 0.01141 -0.0108 0.3586 0.7593 4.250 0.6114 0.02133 0.01173 -0.0111 0.3541 0.8146 4.500 0.6564 0.02156 0.01201 -0.0141 0.3499 0.8736 4.750 0.7064 0.02201 0.01254 -0.0184 0.3451 0.9221 5.000 0.7487 0.02248 0.01307 -0.0215 0.3402 0.9612 5.250 0.7901 0.02287 0.01343 -0.0244 0.3357 0.9891 5.500 0.8234 0.02318 0.01364 -0.0258 0.3322 1.0000 5.750 0.8422 0.02357 0.01396 -0.0244 0.3292 1.0000 6.000 0.8576 0.02408 0.01455 -0.0226 0.3255 1.0000 6.250 0.8747 0.02457 0.01506 -0.0210 0.3221 1.0000 6.500 0.8930 0.02500 0.01548 -0.0196 0.3189 1.0000 6.750 0.9130 0.02537 0.01579 -0.0184 0.3160 1.0000 7.000 0.9347 0.02572 0.01604 -0.0174 0.3135 1.0000 7.250 0.9493 0.02635 0.01675 -0.0157 0.3102 1.0000 7.500 0.9630 0.02701 0.01751 -0.0138 0.3067 1.0000 7.750 0.9789 0.02760 0.01814 -0.0122 0.3035 1.0000 8.000 0.9968 0.02813 0.01867 -0.0109 0.3008 1.0000 8.250 1.0170 0.02858 0.01908 -0.0098 0.2984 1.0000 8.500 1.0399 0.02898 0.01940 -0.0091 0.2961 1.0000 8.750 1.0485 0.02988 0.02044 -0.0069 0.2931 1.0000 9.000 1.0550 0.03085 0.02155 -0.0044 0.2898 1.0000 9.250 1.0647 0.03167 0.02245 -0.0024 0.2868 1.0000 9.500 1.0781 0.03238 0.02318 -0.0008 0.2842 1.0000 9.750 1.0948 0.03298 0.02378 0.0005 0.2820 1.0000 10.000 1.1165 0.03342 0.02417 0.0012 0.2800 1.0000 10.250 1.1225 0.03439 0.02520 0.0036 0.2777 1.0000 10.500 1.1016 0.03635 0.02737 0.0081 0.2747 1.0000 10.750 1.0845 0.03860 0.02978 0.0111 0.2717 1.0000 11.000 1.0759 0.04073 0.03201 0.0128 0.2688 1.0000 11.250 1.0827 0.04209 0.03341 0.0137 0.2664 1.0000 11.500 1.1029 0.04263 0.03393 0.0142 0.2645 1.0000 11.750 1.1355 0.04244 0.03366 0.0145 0.2629 1.0000 12.250 0.9132 0.06938 0.06123 0.0098 0.2468 1.0000