XFOIL Version 6.96 Calculated polar for: EPPLER 333 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.3121 0.08200 0.07924 -0.0389 0.6627 0.0049 -8.500 -0.3139 0.07816 0.07536 -0.0409 0.6471 0.0049 -8.250 -0.3196 0.07397 0.07117 -0.0440 0.6369 0.0049 -8.000 -0.3315 0.07044 0.06761 -0.0455 0.6268 0.0048 -7.750 -0.3405 0.06738 0.06450 -0.0453 0.6167 0.0047 -7.500 -0.3418 0.06413 0.06120 -0.0459 0.6072 0.0045 -7.250 -0.3396 0.06093 0.05791 -0.0462 0.5966 0.0044 -7.000 -0.3386 0.05691 0.05379 -0.0463 0.5880 0.0042 -6.750 -0.3345 0.05300 0.04975 -0.0459 0.5796 0.0040 -6.500 -0.3297 0.04864 0.04523 -0.0450 0.5718 0.0038 -6.000 -0.3243 0.03640 0.03243 -0.0400 0.5601 0.0034 -5.750 -0.3180 0.03047 0.02612 -0.0366 0.5539 0.0034 -5.500 -0.3028 0.02712 0.02249 -0.0344 0.5465 0.0035 -5.250 -0.2880 0.02303 0.01802 -0.0317 0.5393 0.0039 -5.000 -0.2762 0.01679 0.01102 -0.0278 0.5332 0.0044 -4.750 -0.2530 0.01520 0.00910 -0.0267 0.5242 0.0044 -4.500 -0.2282 0.01423 0.00793 -0.0259 0.5152 0.0046 -4.250 -0.2031 0.01340 0.00690 -0.0252 0.5068 0.0046 -4.000 -0.1774 0.01279 0.00616 -0.0247 0.4991 0.0047 -3.750 -0.1514 0.01239 0.00565 -0.0242 0.4912 0.0048 -3.500 -0.1254 0.01199 0.00515 -0.0237 0.4827 0.0049 -3.250 -0.1000 0.01153 0.00458 -0.0231 0.4754 0.0050 -3.000 -0.0753 0.01095 0.00392 -0.0224 0.4681 0.0053 -2.750 -0.0498 0.01063 0.00352 -0.0218 0.4614 0.0054 -2.500 -0.0241 0.01032 0.00316 -0.0213 0.4545 0.0054 -2.000 0.0278 0.00986 0.00259 -0.0203 0.4413 0.0057 -1.750 0.0540 0.00968 0.00236 -0.0199 0.4351 0.0059 -1.500 0.0805 0.00954 0.00218 -0.0195 0.4295 0.0061 -1.250 0.1071 0.00942 0.00201 -0.0192 0.4231 0.0065 -1.000 0.1337 0.00933 0.00187 -0.0188 0.4171 0.0073 -0.750 0.1605 0.00920 0.00174 -0.0185 0.4123 0.0100 -0.500 0.1871 0.00911 0.00166 -0.0182 0.4068 0.0178 -0.250 0.2137 0.00903 0.00160 -0.0179 0.4015 0.0333 0.000 0.2396 0.00884 0.00156 -0.0176 0.3966 0.0829 0.250 0.2546 0.00765 0.00147 -0.0156 0.3923 0.4606 0.500 0.2575 0.00637 0.00156 -0.0102 0.3887 0.8784 0.750 0.2836 0.00645 0.00163 -0.0096 0.3844 0.8968 1.000 0.3089 0.00656 0.00172 -0.0088 0.3796 0.9115 1.250 0.3336 0.00669 0.00181 -0.0079 0.3750 0.9225 1.500 0.3593 0.00679 0.00188 -0.0072 0.3712 0.9295 1.750 0.3848 0.00688 0.00194 -0.0066 0.3668 0.9352 2.000 0.4124 0.00694 0.00196 -0.0065 0.3622 0.9366 2.250 0.4400 0.00702 0.00199 -0.0065 0.3581 0.9376 2.500 0.4680 0.00706 0.00201 -0.0065 0.3542 0.9386 2.750 0.4958 0.00713 0.00204 -0.0065 0.3498 0.9396 3.000 0.5233 0.00721 0.00208 -0.0065 0.3455 0.9406 3.250 0.5510 0.00728 0.00213 -0.0066 0.3417 0.9417 3.500 0.5786 0.00734 0.00217 -0.0066 0.3377 0.9429 3.750 0.6059 0.00742 0.00223 -0.0066 0.3332 0.9441 4.000 0.6332 0.00752 0.00230 -0.0066 0.3290 0.9451 4.250 0.6609 0.00759 0.00236 -0.0066 0.3251 0.9461 4.500 0.6883 0.00767 0.00243 -0.0066 0.3207 0.9470 4.750 0.7153 0.00778 0.00251 -0.0066 0.3156 0.9480 5.000 0.7428 0.00786 0.00260 -0.0066 0.3115 0.9490 5.250 0.7699 0.00795 0.00269 -0.0066 0.3065 0.9500 5.500 0.7964 0.00808 0.00280 -0.0065 0.3010 0.9512 5.750 0.8234 0.00817 0.00290 -0.0065 0.2961 0.9525 6.000 0.8498 0.00830 0.00302 -0.0064 0.2902 0.9539 6.250 0.8762 0.00843 0.00315 -0.0063 0.2843 0.9553 6.500 0.9026 0.00856 0.00327 -0.0062 0.2777 0.9567 6.750 0.9285 0.00872 0.00343 -0.0060 0.2708 0.9582 7.000 0.9546 0.00887 0.00357 -0.0059 0.2642 0.9596 7.250 0.9801 0.00905 0.00374 -0.0057 0.2572 0.9611 7.500 1.0059 0.00922 0.00391 -0.0055 0.2489 0.9626 7.750 1.0314 0.00942 0.00411 -0.0054 0.2400 0.9641 8.000 1.0564 0.00966 0.00433 -0.0051 0.2303 0.9659 8.250 1.0808 0.00995 0.00458 -0.0048 0.2180 0.9680 8.500 1.1051 0.01022 0.00483 -0.0045 0.2069 0.9703 8.750 1.1287 0.01050 0.00510 -0.0041 0.1959 0.9730 9.000 1.1527 0.01083 0.00540 -0.0038 0.1844 0.9755 9.250 1.1776 0.01126 0.00578 -0.0038 0.1694 0.9776 9.500 1.2023 0.01170 0.00617 -0.0039 0.1554 0.9800 9.750 1.2269 0.01214 0.00658 -0.0039 0.1432 0.9827 10.000 1.2490 0.01272 0.00709 -0.0036 0.1269 0.9861 10.250 1.2746 0.01330 0.00763 -0.0041 0.1129 0.9880 10.500 1.2997 0.01390 0.00818 -0.0045 0.1003 0.9904 10.750 1.3225 0.01462 0.00884 -0.0047 0.0845 0.9937 11.000 1.3459 0.01528 0.00946 -0.0049 0.0741 0.9983 11.250 1.3580 0.01593 0.01007 -0.0028 0.0646 1.0000 11.500 1.3659 0.01653 0.01065 0.0001 0.0578 1.0000 11.750 1.3677 0.01735 0.01143 0.0039 0.0473 1.0000 12.000 1.3792 0.01788 0.01200 0.0059 0.0452 1.0000 12.250 1.3848 0.01873 0.01286 0.0085 0.0397 1.0000 12.500 1.3886 0.01977 0.01390 0.0110 0.0333 1.0000 12.750 1.3920 0.02096 0.01510 0.0131 0.0290 1.0000 13.000 1.3908 0.02261 0.01675 0.0151 0.0231 1.0000 13.250 1.3879 0.02465 0.01880 0.0166 0.0178 1.0000 13.500 1.4001 0.02569 0.01995 0.0170 0.0197 1.0000 13.750 1.3983 0.02802 0.02231 0.0177 0.0161 1.0000 14.000 1.3994 0.03027 0.02463 0.0180 0.0146 1.0000 14.250 1.3996 0.03271 0.02714 0.0181 0.0136 1.0000 14.500 1.3993 0.03529 0.02979 0.0180 0.0124 1.0000 14.750 1.3969 0.03815 0.03273 0.0178 0.0112 1.0000 15.000 1.3936 0.04116 0.03582 0.0174 0.0105 1.0000 15.250 1.3813 0.04527 0.03997 0.0169 0.0078 1.0000 15.500 1.3794 0.04825 0.04305 0.0164 0.0080 1.0000 15.750 1.3756 0.05148 0.04636 0.0158 0.0080 1.0000 16.000 1.3649 0.05565 0.05059 0.0149 0.0069 1.0000 16.250 1.3600 0.05922 0.05426 0.0140 0.0068 1.0000 16.500 1.3537 0.06307 0.05819 0.0129 0.0063 1.0000 16.750 1.3444 0.06739 0.06258 0.0116 0.0054 1.0000 17.000 1.3377 0.07146 0.06674 0.0103 0.0053 1.0000 17.250 1.3289 0.07591 0.07126 0.0089 0.0046 1.0000 17.500 1.3245 0.07984 0.07528 0.0075 0.0049 1.0000 17.750 1.3176 0.08415 0.07967 0.0059 0.0045 1.0000 18.000 1.3129 0.08823 0.08384 0.0044 0.0047 1.0000