XFOIL Version 6.96 Calculated polar for: EPPLER 337 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.3921 0.10517 0.10172 -0.0210 1.0000 0.0235 -10.000 -0.3900 0.10132 0.09791 -0.0226 1.0000 0.0234 -9.750 -0.3961 0.09573 0.09238 -0.0268 1.0000 0.0237 -9.500 -0.3980 0.09099 0.08767 -0.0306 1.0000 0.0236 -9.250 -0.3812 0.09139 0.08810 -0.0243 1.0000 0.0252 -9.000 -0.3837 0.08715 0.08392 -0.0267 1.0000 0.0252 -8.750 -0.3865 0.08315 0.07997 -0.0291 1.0000 0.0259 -8.500 -0.3949 0.07861 0.07546 -0.0325 1.0000 0.0261 -8.250 -0.4071 0.07459 0.07145 -0.0336 1.0000 0.0261 -8.000 -0.4112 0.07035 0.06716 -0.0356 0.9323 0.0264 -7.500 -0.3905 0.06073 0.05689 -0.0424 0.8088 0.0272 -7.000 -0.4066 0.04714 0.04237 -0.0361 0.7642 0.0150 -6.750 -0.3989 0.04505 0.04008 -0.0342 0.7420 0.0147 -6.500 -0.3908 0.04254 0.03730 -0.0320 0.7231 0.0144 -6.250 -0.3816 0.03975 0.03421 -0.0295 0.7063 0.0140 -5.750 -0.3600 0.03308 0.02673 -0.0239 0.6778 0.0130 -5.500 -0.3477 0.02778 0.02049 -0.0197 0.6666 0.0119 -5.250 -0.3283 0.02587 0.01821 -0.0180 0.6532 0.0118 -5.000 -0.3068 0.02404 0.01598 -0.0166 0.6402 0.0118 -4.750 -0.2831 0.02245 0.01403 -0.0155 0.6277 0.0118 -4.500 -0.2578 0.02110 0.01240 -0.0147 0.6155 0.0119 -4.250 -0.2322 0.01989 0.01098 -0.0141 0.6039 0.0121 -4.000 -0.2067 0.01896 0.00988 -0.0135 0.5926 0.0123 -3.750 -0.1812 0.01817 0.00897 -0.0129 0.5814 0.0127 -3.500 -0.1563 0.01747 0.00816 -0.0121 0.5712 0.0133 -3.250 -0.1321 0.01683 0.00739 -0.0112 0.5619 0.0140 -3.000 -0.1083 0.01626 0.00672 -0.0103 0.5521 0.0148 -2.750 -0.0851 0.01582 0.00621 -0.0093 0.5431 0.0160 -2.500 -0.0612 0.01548 0.00580 -0.0085 0.5339 0.0192 -2.250 -0.0376 0.01515 0.00540 -0.0076 0.5257 0.0224 -2.000 -0.0145 0.01477 0.00496 -0.0065 0.5177 0.0288 -1.750 0.0081 0.01438 0.00463 -0.0054 0.5105 0.0470 -1.500 0.0296 0.01394 0.00437 -0.0042 0.5027 0.0987 -1.250 0.0707 0.01213 0.00546 -0.0056 0.4948 0.8511 -1.000 0.0753 0.01247 0.00570 -0.0001 0.4886 0.8864 -0.750 0.1417 0.01358 0.00654 -0.0062 0.4801 0.9140 -0.500 0.1978 0.01421 0.00697 -0.0110 0.4714 0.9324 -0.250 0.2496 0.01443 0.00699 -0.0156 0.4639 0.9397 0.000 0.2780 0.01442 0.00688 -0.0158 0.4574 0.9427 0.250 0.3015 0.01446 0.00679 -0.0150 0.4522 0.9465 0.500 0.3270 0.01447 0.00671 -0.0146 0.4470 0.9493 0.750 0.3587 0.01445 0.00660 -0.0155 0.4408 0.9508 1.000 0.3887 0.01447 0.00649 -0.0161 0.4355 0.9526 1.250 0.4179 0.01448 0.00645 -0.0165 0.4303 0.9546 1.500 0.4452 0.01451 0.00642 -0.0166 0.4253 0.9567 1.750 0.4703 0.01457 0.00639 -0.0162 0.4208 0.9592 2.000 0.4918 0.01464 0.00642 -0.0150 0.4166 0.9619 2.250 0.5209 0.01465 0.00641 -0.0155 0.4114 0.9632 2.500 0.5507 0.01469 0.00639 -0.0161 0.4070 0.9644 2.750 0.5788 0.01475 0.00638 -0.0164 0.4030 0.9657 3.000 0.6072 0.01479 0.00644 -0.0167 0.3981 0.9673 3.250 0.6342 0.01486 0.00651 -0.0168 0.3938 0.9689 3.500 0.6597 0.01495 0.00655 -0.0165 0.3900 0.9703 3.750 0.6847 0.01505 0.00664 -0.0162 0.3860 0.9721 4.000 0.7081 0.01515 0.00677 -0.0155 0.3815 0.9739 4.250 0.7327 0.01524 0.00688 -0.0150 0.3776 0.9750 4.500 0.7610 0.01534 0.00694 -0.0154 0.3738 0.9760 4.750 0.7892 0.01544 0.00707 -0.0158 0.3696 0.9772 5.000 0.8160 0.01554 0.00722 -0.0159 0.3652 0.9783 5.250 0.8417 0.01566 0.00737 -0.0158 0.3612 0.9793 5.500 0.8672 0.01582 0.00750 -0.0156 0.3575 0.9805 5.750 0.8929 0.01595 0.00772 -0.0155 0.3531 0.9819 6.000 0.9172 0.01609 0.00794 -0.0151 0.3487 0.9832 6.250 0.9404 0.01626 0.00812 -0.0145 0.3447 0.9843 6.500 0.9629 0.01645 0.00834 -0.0137 0.3410 0.9854 6.750 0.9896 0.01659 0.00860 -0.0139 0.3359 0.9864 7.000 1.0165 0.01674 0.00880 -0.0141 0.3306 0.9875 7.250 1.0419 0.01692 0.00901 -0.0140 0.3258 0.9885 7.500 1.0664 0.01710 0.00932 -0.0138 0.3201 0.9895 7.750 1.0903 0.01730 0.00957 -0.0134 0.3152 0.9906 8.000 1.1138 0.01753 0.00986 -0.0130 0.3106 0.9916 8.250 1.1370 0.01774 0.01022 -0.0126 0.3047 0.9928 8.500 1.1601 0.01798 0.01049 -0.0121 0.2987 0.9942 8.750 1.1845 0.01821 0.01086 -0.0120 0.2914 0.9954 9.000 1.2077 0.01846 0.01118 -0.0117 0.2848 0.9965 9.250 1.2306 0.01874 0.01158 -0.0113 0.2772 0.9977 9.500 1.2523 0.01906 0.01194 -0.0108 0.2698 0.9990 9.750 1.2733 0.01939 0.01241 -0.0101 0.2611 1.0000 10.000 1.2857 0.01976 0.01284 -0.0078 0.2536 1.0000 10.250 1.2973 0.02015 0.01332 -0.0053 0.2447 1.0000 10.500 1.3067 0.02058 0.01382 -0.0025 0.2365 1.0000 10.750 1.3127 0.02106 0.01434 0.0008 0.2280 1.0000 11.000 1.3170 0.02155 0.01491 0.0044 0.2187 1.0000 11.250 1.3162 0.02209 0.01549 0.0088 0.2108 1.0000 11.500 1.3075 0.02258 0.01603 0.0147 0.2032 1.0000 11.750 1.2946 0.02312 0.01659 0.0210 0.1972 1.0000 12.000 1.2850 0.02382 0.01734 0.0262 0.1898 1.0000 12.250 1.2780 0.02480 0.01834 0.0302 0.1821 1.0000 12.500 1.2715 0.02617 0.01973 0.0333 0.1735 1.0000 12.750 1.2692 0.02772 0.02134 0.0352 0.1647 1.0000 13.000 1.2646 0.02970 0.02335 0.0366 0.1560 1.0000 13.250 1.2581 0.03212 0.02579 0.0376 0.1474 1.0000 13.500 1.2542 0.03455 0.02830 0.0381 0.1395 1.0000 13.750 1.2464 0.03751 0.03129 0.0383 0.1328 1.0000 14.000 1.2390 0.04059 0.03443 0.0382 0.1250 1.0000 14.250 1.2300 0.04395 0.03785 0.0380 0.1188 1.0000 14.500 1.2201 0.04751 0.04145 0.0375 0.1129 1.0000 14.750 1.2117 0.05100 0.04502 0.0370 0.1070 1.0000 15.000 1.2008 0.05487 0.04893 0.0363 0.1019 1.0000 15.250 1.1922 0.05862 0.05275 0.0354 0.0964 1.0000 15.500 1.1831 0.06257 0.05676 0.0344 0.0914 1.0000 15.750 1.1732 0.06675 0.06098 0.0332 0.0870 1.0000 16.000 1.1667 0.07059 0.06490 0.0321 0.0823 1.0000 16.250 1.1580 0.07481 0.06916 0.0307 0.0780 1.0000 16.500 1.1497 0.07907 0.07348 0.0293 0.0743 1.0000 16.750 1.1443 0.08303 0.07752 0.0279 0.0700 1.0000 17.000 1.1351 0.08759 0.08212 0.0262 0.0661 1.0000 17.250 1.1291 0.09178 0.08639 0.0247 0.0623 1.0000