XFOIL Version 6.96 Calculated polar for: EPPLER 715 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.7415 0.12099 0.11901 -0.0024 1.0000 0.0048 -16.000 -0.7719 0.10934 0.10721 -0.0090 1.0000 0.0046 -15.750 -0.7982 0.09918 0.09691 -0.0150 1.0000 0.0045 -15.500 -0.8241 0.08961 0.08719 -0.0206 1.0000 0.0044 -15.250 -0.8469 0.08104 0.07847 -0.0258 1.0000 0.0044 -15.000 -0.8617 0.07429 0.07160 -0.0299 1.0000 0.0044 -14.750 -0.8799 0.06731 0.06448 -0.0341 1.0000 0.0044 -14.500 -0.8952 0.06140 0.05845 -0.0376 1.0000 0.0044 -14.250 -0.9075 0.05634 0.05327 -0.0404 1.0000 0.0043 -14.000 -0.9218 0.05125 0.04806 -0.0432 1.0000 0.0044 -13.750 -0.9290 0.04728 0.04399 -0.0452 1.0000 0.0044 -13.500 -0.9405 0.04298 0.03957 -0.0472 1.0000 0.0043 -13.250 -0.9324 0.03920 0.03532 -0.0522 0.8354 0.0044 -13.000 -0.9417 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0.5468 0.3215 -3.500 -0.1591 0.00761 0.00194 -0.0407 0.5449 0.3572 -3.250 -0.1307 0.00748 0.00188 -0.0408 0.5430 0.3880 -3.000 -0.1019 0.00743 0.00185 -0.0409 0.5411 0.4116 -2.750 -0.0731 0.00743 0.00184 -0.0410 0.5388 0.4272 -2.500 -0.0440 0.00746 0.00185 -0.0411 0.5366 0.4392 -2.250 -0.0147 0.00744 0.00184 -0.0412 0.5351 0.4482 -2.000 0.0146 0.00745 0.00183 -0.0414 0.5335 0.4564 -1.750 0.0438 0.00746 0.00184 -0.0415 0.5317 0.4634 -1.500 0.0732 0.00749 0.00183 -0.0417 0.5299 0.4695 -1.250 0.1023 0.00748 0.00183 -0.0419 0.5280 0.4751 -1.000 0.1315 0.00751 0.00183 -0.0420 0.5261 0.4801 -0.750 0.1608 0.00758 0.00185 -0.0422 0.5241 0.4845 -0.500 0.1896 0.00764 0.00188 -0.0423 0.5218 0.4887 -0.250 0.2189 0.00763 0.00190 -0.0425 0.5205 0.4932 0.000 0.2482 0.00765 0.00191 -0.0427 0.5189 0.4975 0.250 0.2776 0.00768 0.00193 -0.0429 0.5171 0.5009 0.500 0.3066 0.00766 0.00193 -0.0430 0.5153 0.5046 0.750 0.3357 0.00766 0.00194 -0.0432 0.5135 0.5080 1.000 0.3648 0.00769 0.00196 -0.0434 0.5116 0.5116 1.250 0.3939 0.00774 0.00200 -0.0436 0.5096 0.5152 1.500 0.4227 0.00782 0.00205 -0.0437 0.5072 0.5184 1.750 0.4517 0.00781 0.00208 -0.0439 0.5055 0.5217 2.000 0.4808 0.00781 0.00211 -0.0441 0.5036 0.5247 2.250 0.5099 0.00781 0.00214 -0.0443 0.5014 0.5276 2.500 0.5390 0.00782 0.00216 -0.0445 0.4989 0.5304 2.750 0.5681 0.00784 0.00218 -0.0446 0.4964 0.5329 3.000 0.5967 0.00785 0.00220 -0.0448 0.4935 0.5362 3.250 0.6254 0.00790 0.00227 -0.0449 0.4906 0.5391 3.500 0.6545 0.00788 0.00231 -0.0451 0.4880 0.5422 3.750 0.6835 0.00789 0.00234 -0.0453 0.4849 0.5453 4.000 0.7124 0.00790 0.00237 -0.0455 0.4817 0.5479 4.250 0.7408 0.00792 0.00241 -0.0456 0.4782 0.5515 4.500 0.7694 0.00795 0.00248 -0.0458 0.4748 0.5551 4.750 0.7983 0.00794 0.00254 -0.0460 0.4712 0.5589 5.000 0.8271 0.00796 0.00259 -0.0462 0.4672 0.5623 5.250 0.8553 0.00801 0.00265 -0.0463 0.4628 0.5665 5.500 0.8839 0.00801 0.00273 -0.0464 0.4581 0.5713 5.750 0.9124 0.00802 0.00280 -0.0466 0.4526 0.5765 6.000 0.9403 0.00809 0.00288 -0.0467 0.4468 0.5821 6.250 0.9688 0.00810 0.00297 -0.0468 0.4403 0.5890 6.500 0.9965 0.00817 0.00307 -0.0469 0.4326 0.5970 6.750 1.0245 0.00821 0.00319 -0.0470 0.4232 0.6085 7.000 1.0517 0.00829 0.00333 -0.0470 0.4114 0.6259 7.250 1.0782 0.00837 0.00350 -0.0469 0.3971 0.6592 7.500 1.0964 0.00802 0.00374 -0.0451 0.3780 0.8867 7.750 1.1376 0.00841 0.00410 -0.0484 0.3447 1.0000 8.000 1.1601 0.00898 0.00452 -0.0478 0.3100 1.0000 8.250 1.1805 0.00972 0.00506 -0.0471 0.2720 1.0000 8.500 1.2009 0.01042 0.00559 -0.0463 0.2387 1.0000 8.750 1.2207 0.01113 0.00615 -0.0454 0.2088 1.0000 9.000 1.2398 0.01184 0.00673 -0.0445 0.1825 1.0000 9.250 1.2582 0.01255 0.00732 -0.0434 0.1587 1.0000 9.500 1.2758 0.01326 0.00793 -0.0423 0.1377 1.0000 9.750 1.2919 0.01401 0.00858 -0.0410 0.1192 1.0000 10.250 1.3185 0.01560 0.01001 -0.0377 0.0887 1.0000 10.500 1.3266 0.01645 0.01082 -0.0353 0.0770 1.0000 10.750 1.3289 0.01732 0.01168 -0.0320 0.0691 1.0000 11.000 1.3304 0.01851 0.01288 -0.0296 0.0618 1.0000 11.250 1.3314 0.02013 0.01448 -0.0279 0.0547 1.0000 11.500 1.3367 0.02172 0.01609 -0.0269 0.0494 1.0000 11.750 1.3406 0.02354 0.01792 -0.0261 0.0440 1.0000 12.000 1.3433 0.02553 0.01990 -0.0254 0.0386 1.0000 12.250 1.3485 0.02736 0.02175 -0.0248 0.0349 1.0000 12.500 1.3515 0.02938 0.02379 -0.0241 0.0313 1.0000 12.750 1.3553 0.03134 0.02577 -0.0235 0.0281 1.0000 13.000 1.3591 0.03333 0.02778 -0.0230 0.0258 1.0000 13.250 1.3604 0.03553 0.03001 -0.0224 0.0232 1.0000 13.500 1.3648 0.03750 0.03201 -0.0220 0.0214 1.0000 13.750 1.3670 0.03968 0.03421 -0.0216 0.0197 1.0000 14.000 1.3693 0.04184 0.03641 -0.0212 0.0178 1.0000 14.250 1.3721 0.04401 0.03863 -0.0209 0.0165 1.0000 14.500 1.3735 0.04642 0.04106 -0.0207 0.0151 1.0000 14.750 1.3770 0.04868 0.04337 -0.0205 0.0140 1.0000 15.000 1.3804 0.05102 0.04576 -0.0205 0.0130 1.0000 15.250 1.3824 0.05352 0.04830 -0.0205 0.0121 1.0000 15.500 1.3832 0.05624 0.05106 -0.0206 0.0109 1.0000 15.750 1.3871 0.05863 0.05352 -0.0207 0.0103 1.0000 16.000 1.3886 0.06136 0.05629 -0.0210 0.0096 1.0000 16.250 1.3864 0.06456 0.05953 -0.0213 0.0085 1.0000 16.500 1.3892 0.06723 0.06227 -0.0217 0.0080 1.0000 16.750 1.3908 0.07011 0.06520 -0.0221 0.0074 1.0000 17.000 1.3902 0.07329 0.06844 -0.0227 0.0070 1.0000 17.250 1.3847 0.07721 0.07242 -0.0235 0.0063 1.0000 17.500 1.3866 0.08022 0.07551 -0.0242 0.0061 1.0000 17.750 1.3854 0.08372 0.07910 -0.0251 0.0059 1.0000 18.000 1.3838 0.08732 0.08277 -0.0261 0.0055 1.0000 18.250 1.3826 0.09090 0.08641 -0.0272 0.0052 1.0000 18.500 1.3753 0.09552 0.09111 -0.0287 0.0049 1.0000