XFOIL Version 6.96 Calculated polar for: EPPLER STE 871-514 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5299 0.09681 0.09378 -0.0403 1.0020 0.0429 -9.000 -0.5542 0.09194 0.08888 -0.0408 1.0020 0.0429 -8.750 -0.5767 0.08813 0.08504 -0.0397 1.0020 0.0429 -8.500 -0.6020 0.08498 0.08186 -0.0372 1.0020 0.0429 -8.250 -0.6255 0.08235 0.07922 -0.0338 1.0020 0.0429 -8.000 -0.6532 0.07854 0.07527 -0.0313 1.0020 0.0429 -7.750 -0.6472 0.07546 0.07228 -0.0297 1.0020 0.0434 -7.500 -0.6513 0.07267 0.06949 -0.0277 1.0020 0.0440 -7.250 -0.6589 0.06944 0.06620 -0.0258 1.0020 0.0448 -7.000 -0.6684 0.06544 0.06202 -0.0241 1.0020 0.0464 -6.750 -0.7105 0.06292 0.05863 -0.0233 1.0020 0.0479 -6.500 -0.7001 0.06041 0.05621 -0.0224 1.0020 0.0488 -6.250 -0.6933 0.05682 0.05222 -0.0215 1.0020 0.0532 -6.000 -0.6804 0.05483 0.05031 -0.0208 1.0020 0.0555 -5.750 -0.6680 0.05180 0.04703 -0.0202 1.0020 0.0601 -5.500 -0.6468 0.04892 0.04386 -0.0210 1.0006 0.0657 -5.250 -0.6202 0.04633 0.04099 -0.0227 0.9984 0.0721 -5.000 -0.5932 0.04414 0.03857 -0.0242 0.9966 0.0793 -4.750 -0.5664 0.04208 0.03631 -0.0254 0.9935 0.0875 -4.500 -0.5351 0.04039 0.03446 -0.0275 0.9910 0.0979 -4.250 -0.4856 0.03160 0.02366 -0.0239 0.9913 0.0347 -4.000 -0.4522 0.03038 0.02228 -0.0248 0.9901 0.0333 -3.750 -0.4259 0.02905 0.02079 -0.0245 0.9867 0.0328 -3.500 -0.3927 0.02828 0.01986 -0.0255 0.9844 0.0332 -3.250 -0.3576 0.02788 0.01938 -0.0270 0.9828 0.0350 -3.000 -0.3305 0.02741 0.01890 -0.0274 0.9776 0.0383 -2.750 -0.2912 0.02715 0.01873 -0.0301 0.9750 0.0411 -2.250 -0.2179 0.02636 0.01803 -0.0347 0.9604 0.0531 -2.000 -0.1435 0.02443 0.01926 -0.0434 0.9404 0.7681 -1.750 -0.1229 0.02587 0.02068 -0.0396 0.9337 0.8051 -1.500 -0.1173 0.02635 0.02118 -0.0331 0.9227 0.8274 -1.250 -0.1161 0.02682 0.02166 -0.0252 0.9118 0.8568 -1.000 -0.1183 0.02727 0.02214 -0.0153 0.9061 0.8914 -0.750 -0.1280 0.02681 0.02168 -0.0058 0.8945 0.9154 -0.500 -0.1009 0.02694 0.02172 -0.0045 0.8910 0.9306 -0.250 -0.0847 0.02666 0.02136 -0.0030 0.8812 0.9339 0.000 -0.0480 0.02674 0.02132 -0.0053 0.8772 0.9353 0.250 -0.0059 0.02694 0.02143 -0.0085 0.8748 0.9361 0.500 0.0085 0.02664 0.02109 -0.0067 0.8645 0.9380 0.750 0.0460 0.02664 0.02102 -0.0090 0.8609 0.9388 1.000 0.0878 0.02672 0.02104 -0.0120 0.8586 0.9393 1.250 0.1029 0.02651 0.02081 -0.0104 0.8480 0.9412 1.500 0.1418 0.02646 0.02072 -0.0129 0.8446 0.9414 1.750 0.1837 0.02642 0.02064 -0.0158 0.8425 0.9418 2.000 0.1999 0.02628 0.02051 -0.0144 0.8318 0.9434 2.250 0.2401 0.02610 0.02032 -0.0170 0.8286 0.9435 2.500 0.2837 0.02586 0.02008 -0.0200 0.8265 0.9433 2.750 0.3015 0.02571 0.01995 -0.0189 0.8155 0.9447 3.000 0.3435 0.02529 0.01954 -0.0214 0.8125 0.9451 3.250 0.3891 0.02473 0.01901 -0.0245 0.8106 0.9451 3.500 0.4092 0.02446 0.01878 -0.0236 0.7987 0.9458 3.750 0.4552 0.02363 0.01800 -0.0265 0.7961 0.9457 4.000 0.4801 0.02317 0.01759 -0.0262 0.7846 0.9462 4.250 0.5271 0.02193 0.01640 -0.0288 0.7810 0.9464 4.500 0.5547 0.02115 0.01568 -0.0284 0.7685 0.9475 4.750 0.5886 0.02014 0.01476 -0.0289 0.7581 0.9481 5.000 0.6261 0.01897 0.01366 -0.0299 0.7500 0.9484 5.250 0.6542 0.01835 0.01310 -0.0298 0.7350 0.9489 5.500 0.6882 0.01752 0.01235 -0.0304 0.7178 0.9493 5.750 0.7273 0.01651 0.01136 -0.0317 0.6924 0.9496 6.000 0.7884 0.01483 0.00945 -0.0361 0.6392 0.9491 6.250 0.8183 0.01483 0.00908 -0.0361 0.5580 0.9495 6.500 0.8263 0.01564 0.00942 -0.0330 0.4746 0.9505 6.750 0.8289 0.01672 0.01006 -0.0294 0.3945 0.9521 7.000 0.8309 0.01788 0.01079 -0.0258 0.3158 0.9540 7.250 0.8353 0.01914 0.01161 -0.0229 0.2396 0.9554 7.500 0.8432 0.02040 0.01248 -0.0207 0.1817 0.9567 7.750 0.8558 0.02146 0.01332 -0.0191 0.1497 0.9580 8.000 0.8706 0.02240 0.01414 -0.0178 0.1320 0.9593 8.250 0.8870 0.02329 0.01495 -0.0168 0.1205 0.9608 8.500 0.9050 0.02411 0.01577 -0.0160 0.1120 0.9623 8.750 0.9234 0.02496 0.01660 -0.0153 0.1054 0.9639 9.000 0.9424 0.02586 0.01742 -0.0147 0.1000 0.9656 9.250 0.9640 0.02659 0.01824 -0.0144 0.0953 0.9675 9.500 0.9872 0.02751 0.01904 -0.0144 0.0914 0.9692 9.750 1.0102 0.02823 0.01991 -0.0143 0.0876 0.9717 10.000 1.0375 0.02909 0.02069 -0.0149 0.0842 0.9743 10.250 1.0649 0.02997 0.02169 -0.0154 0.0814 0.9780 10.500 1.0917 0.03082 0.02259 -0.0160 0.0785 0.9832 10.750 1.1247 0.03184 0.02360 -0.0174 0.0759 0.9948 11.000 1.1525 0.03297 0.02494 -0.0181 0.0736 0.9980 11.250 1.1826 0.03411 0.02611 -0.0193 0.0712 0.9980 11.500 1.2153 0.03566 0.02780 -0.0208 0.0691 0.9980 11.750 1.2366 0.03712 0.02951 -0.0207 0.0671 0.9980 12.000 1.2653 0.03842 0.03085 -0.0218 0.0649 0.9980 12.250 1.2875 0.04033 0.03296 -0.0220 0.0631 0.9980 12.500 1.2958 0.04203 0.03500 -0.0202 0.0613 0.9980 12.750 1.3193 0.04326 0.03622 -0.0207 0.0592 0.9980 13.000 1.3287 0.04529 0.03850 -0.0194 0.0576 0.9980 13.250 1.3254 0.04738 0.04095 -0.0164 0.0561 0.9980 13.500 1.3386 0.04874 0.04238 -0.0157 0.0543 0.9980 13.750 1.3502 0.05068 0.04442 -0.0150 0.0526 0.9980 14.000 1.3335 0.05345 0.04763 -0.0111 0.0516 0.9980 14.250 1.3250 0.05603 0.05049 -0.0084 0.0504 0.9980 14.500 1.3610 0.05642 0.05059 -0.0105 0.0482 0.9980 14.750 1.3332 0.05995 0.05458 -0.0063 0.0477 0.9980 15.000 1.3076 0.06391 0.05894 -0.0032 0.0471 0.9980 15.250 1.2840 0.06809 0.06345 -0.0010 0.0464 0.9980 15.500 1.2626 0.07241 0.06804 0.0004 0.0459 0.9980 15.750 1.2486 0.07625 0.07206 0.0008 0.0451 0.9980 16.000 1.2728 0.07651 0.07217 0.0004 0.0434 0.9980 16.250 1.2407 0.08252 0.07849 0.0004 0.0432 0.9980 16.500 1.2093 0.08926 0.08551 -0.0010 0.0432 0.9980 16.750 1.1777 0.09684 0.09335 -0.0037 0.0432 0.9980 17.000 1.1474 0.10511 0.10182 -0.0077 0.0434 0.9980 17.250 1.1179 0.11418 0.11107 -0.0129 0.0435 0.9980