XFOIL Version 6.96 Calculated polar for: EPPLER 332 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.3896 0.09179 0.08938 -0.0220 0.7441 0.0057 -9.250 -0.3946 0.08718 0.08471 -0.0239 0.7213 0.0058 -7.750 -0.4269 0.06449 0.06169 -0.0325 0.6346 0.0057 -5.250 -0.3681 0.02277 0.01774 -0.0132 0.5449 0.0037 -5.000 -0.3544 0.01849 0.01287 -0.0101 0.5367 0.0035 -4.750 -0.3322 0.01662 0.01067 -0.0087 0.5277 0.0035 -4.500 -0.3083 0.01517 0.00892 -0.0077 0.5191 0.0034 -4.250 -0.2836 0.01394 0.00745 -0.0068 0.5093 0.0034 -4.000 -0.2583 0.01318 0.00652 -0.0061 0.5009 0.0034 -3.750 -0.2333 0.01241 0.00560 -0.0054 0.4919 0.0034 -3.500 -0.2079 0.01188 0.00496 -0.0047 0.4845 0.0034 -3.000 -0.1577 0.01097 0.00385 -0.0033 0.4680 0.0034 -2.750 -0.1324 0.01065 0.00345 -0.0027 0.4603 0.0034 -2.500 -0.1068 0.01034 0.00308 -0.0021 0.4537 0.0035 -2.250 -0.0811 0.01011 0.00279 -0.0016 0.4468 0.0036 -2.000 -0.0550 0.00990 0.00253 -0.0011 0.4405 0.0036 -1.750 -0.0291 0.00969 0.00226 -0.0006 0.4335 0.0039 -1.500 -0.0029 0.00953 0.00206 -0.0002 0.4271 0.0042 -1.250 0.0237 0.00942 0.00191 0.0002 0.4206 0.0051 -1.000 0.0503 0.00934 0.00179 0.0005 0.4150 0.0059 -0.750 0.0770 0.00922 0.00168 0.0008 0.4094 0.0104 -0.500 0.1033 0.00911 0.00160 0.0012 0.4032 0.0247 -0.250 0.1292 0.00895 0.00154 0.0016 0.3978 0.0577 0.000 0.1501 0.00831 0.00147 0.0027 0.3930 0.2456 0.250 0.1397 0.00614 0.00141 0.0104 0.3898 0.8690 0.500 0.1652 0.00625 0.00151 0.0112 0.3847 0.8954 0.750 0.1917 0.00634 0.00158 0.0117 0.3795 0.9069 1.000 0.2168 0.00648 0.00168 0.0126 0.3744 0.9195 1.250 0.2430 0.00661 0.00178 0.0132 0.3698 0.9269 1.500 0.2686 0.00671 0.00185 0.0139 0.3650 0.9333 1.750 0.2963 0.00678 0.00188 0.0140 0.3599 0.9351 2.000 0.3242 0.00685 0.00189 0.0140 0.3553 0.9361 2.250 0.3523 0.00690 0.00191 0.0139 0.3506 0.9370 2.500 0.3801 0.00696 0.00193 0.0139 0.3458 0.9379 2.750 0.4078 0.00703 0.00196 0.0139 0.3413 0.9388 3.000 0.4356 0.00708 0.00200 0.0138 0.3367 0.9399 3.250 0.4632 0.00715 0.00204 0.0138 0.3321 0.9410 3.500 0.4905 0.00724 0.00209 0.0139 0.3273 0.9421 3.750 0.5182 0.00730 0.00213 0.0138 0.3230 0.9430 4.000 0.5456 0.00737 0.00219 0.0138 0.3183 0.9440 4.250 0.5727 0.00747 0.00226 0.0138 0.3132 0.9450 4.500 0.6002 0.00754 0.00232 0.0138 0.3090 0.9459 4.750 0.6275 0.00763 0.00239 0.0138 0.3039 0.9468 5.000 0.6547 0.00774 0.00248 0.0138 0.2986 0.9477 5.250 0.6823 0.00782 0.00258 0.0137 0.2939 0.9487 5.500 0.7094 0.00793 0.00268 0.0138 0.2882 0.9498 5.750 0.7363 0.00805 0.00279 0.0138 0.2826 0.9508 6.000 0.7633 0.00816 0.00291 0.0138 0.2769 0.9519 6.500 0.8166 0.00842 0.00316 0.0139 0.2644 0.9542 6.750 0.8427 0.00859 0.00332 0.0140 0.2569 0.9555 7.000 0.8691 0.00872 0.00346 0.0141 0.2502 0.9568 7.250 0.8947 0.00891 0.00362 0.0143 0.2414 0.9582 7.500 0.9202 0.00910 0.00380 0.0145 0.2320 0.9596 7.750 0.9454 0.00929 0.00399 0.0147 0.2234 0.9610 8.000 0.9706 0.00955 0.00421 0.0149 0.2110 0.9624 8.250 0.9958 0.00982 0.00446 0.0151 0.2001 0.9640 8.500 1.0205 0.01012 0.00473 0.0153 0.1884 0.9658 8.750 1.0443 0.01046 0.00504 0.0156 0.1744 0.9678 9.250 1.0901 0.01120 0.00571 0.0166 0.1479 0.9723 9.500 1.1123 0.01160 0.00608 0.0172 0.1360 0.9748 9.750 1.1368 0.01209 0.00652 0.0171 0.1208 0.9765 10.000 1.1605 0.01267 0.00703 0.0171 0.1044 0.9785 10.250 1.1843 0.01320 0.00753 0.0171 0.0923 0.9808 10.500 1.2061 0.01384 0.00810 0.0173 0.0787 0.9837 10.750 1.2283 0.01443 0.00868 0.0175 0.0682 0.9864 11.000 1.2525 0.01518 0.00937 0.0170 0.0565 0.9880 11.250 1.2764 0.01588 0.01005 0.0165 0.0476 0.9899 11.500 1.2967 0.01686 0.01096 0.0163 0.0352 0.9926 11.750 1.3199 0.01747 0.01161 0.0161 0.0322 0.9957 12.000 1.3361 0.01828 0.01243 0.0168 0.0271 1.0000 12.250 1.3282 0.01906 0.01320 0.0221 0.0220 1.0000 12.500 1.3368 0.01964 0.01385 0.0245 0.0225 1.0000 12.750 1.3402 0.02063 0.01488 0.0269 0.0196 1.0000 13.000 1.3366 0.02228 0.01652 0.0292 0.0143 1.0000 13.250 1.3408 0.02371 0.01802 0.0304 0.0134 1.0000 13.500 1.3417 0.02562 0.01997 0.0312 0.0111 1.0000 13.750 1.3403 0.02797 0.02236 0.0316 0.0089 1.0000 14.000 1.3450 0.02991 0.02439 0.0317 0.0090 1.0000 14.250 1.3467 0.03224 0.02679 0.0315 0.0084 1.0000 14.500 1.3458 0.03492 0.02955 0.0313 0.0076 1.0000 14.750 1.3434 0.03784 0.03256 0.0309 0.0070 1.0000 15.000 1.3382 0.04111 0.03591 0.0303 0.0061 1.0000 15.250 1.3356 0.04413 0.03902 0.0298 0.0061 1.0000 15.500 1.3306 0.04748 0.04245 0.0291 0.0057 1.0000 15.750 1.3223 0.05123 0.04628 0.0283 0.0051 1.0000 16.000 1.3192 0.05442 0.04957 0.0275 0.0055 1.0000 16.250 1.3057 0.05901 0.05422 0.0262 0.0043 1.0000 16.500 1.2995 0.06281 0.05811 0.0251 0.0044 1.0000 16.750 1.2908 0.06705 0.06243 0.0238 0.0038 1.0000 17.000 1.2836 0.07114 0.06661 0.0225 0.0038 1.0000 17.250 1.2770 0.07523 0.07078 0.0211 0.0037 1.0000 17.500 1.2705 0.07943 0.07506 0.0196 0.0037 1.0000 17.750 1.2631 0.08378 0.07950 0.0180 0.0037 1.0000 18.000 1.2520 0.08873 0.08452 0.0161 0.0031 1.0000