XFOIL Version 6.96 Calculated polar for: EPPLER 360 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.4359 0.07859 0.07644 -0.0325 1.0000 0.0220 -10.250 -0.4445 0.07267 0.07053 -0.0351 1.0000 0.0222 -9.000 -0.6084 0.04095 0.03812 -0.0399 1.0000 0.0219 -8.750 -0.6096 0.03821 0.03536 -0.0378 1.0000 0.0221 -8.500 -0.6105 0.03589 0.03301 -0.0353 1.0000 0.0223 -8.250 -0.6127 0.03347 0.03051 -0.0324 1.0000 0.0225 -8.000 -0.6127 0.03127 0.02825 -0.0295 1.0000 0.0228 -7.750 -0.6131 0.02916 0.02606 -0.0263 1.0000 0.0233 -7.000 -0.6294 0.02310 0.01753 -0.0154 0.9879 0.0142 -6.750 -0.5945 0.02117 0.01543 -0.0170 0.9830 0.0136 -6.500 -0.5623 0.01902 0.01308 -0.0181 0.9750 0.0132 -6.250 -0.5295 0.01734 0.01123 -0.0192 0.9644 0.0129 -6.000 -0.4942 0.01595 0.00971 -0.0207 0.9525 0.0129 -5.750 -0.4570 0.01477 0.00842 -0.0227 0.9379 0.0132 -5.500 -0.4212 0.01385 0.00740 -0.0244 0.9179 0.0134 -5.250 -0.3932 0.01317 0.00658 -0.0243 0.8921 0.0140 -5.000 -0.3721 0.01245 0.00575 -0.0230 0.8672 0.0147 -4.750 -0.3495 0.01206 0.00527 -0.0218 0.8459 0.0159 -4.500 -0.3273 0.01164 0.00473 -0.0205 0.8268 0.0179 -4.250 -0.3044 0.01130 0.00431 -0.0194 0.8097 0.0212 -4.000 -0.2820 0.01087 0.00387 -0.0183 0.7945 0.0306 -3.750 -0.2599 0.01042 0.00351 -0.0171 0.7808 0.0578 -3.500 -0.2375 0.01001 0.00323 -0.0161 0.7680 0.0992 -3.250 -0.2168 0.00945 0.00296 -0.0149 0.7557 0.1789 -3.000 -0.1999 0.00857 0.00266 -0.0132 0.7444 0.3309 -2.750 -0.1883 0.00747 0.00237 -0.0105 0.7342 0.5398 -2.500 -0.1717 0.00695 0.00234 -0.0080 0.7242 0.6804 -2.250 -0.1479 0.00688 0.00237 -0.0068 0.7148 0.7332 -2.000 -0.1224 0.00691 0.00238 -0.0060 0.7063 0.7607 -1.750 -0.0960 0.00694 0.00238 -0.0054 0.6973 0.7797 -1.250 -0.0432 0.00706 0.00242 -0.0043 0.6814 0.8099 -1.000 -0.0173 0.00717 0.00249 -0.0035 0.6743 0.8259 -0.750 0.0086 0.00725 0.00258 -0.0027 0.6667 0.8405 -0.500 0.0345 0.00734 0.00263 -0.0020 0.6598 0.8521 -0.250 0.0609 0.00743 0.00269 -0.0014 0.6529 0.8619 0.000 0.0876 0.00748 0.00271 -0.0009 0.6459 0.8694 0.250 0.1144 0.00755 0.00274 -0.0005 0.6393 0.8765 0.500 0.1411 0.00756 0.00273 -0.0001 0.6311 0.8823 0.750 0.1683 0.00761 0.00273 0.0002 0.6226 0.8869 1.000 0.1950 0.00763 0.00271 0.0005 0.6126 0.8921 1.250 0.2214 0.00763 0.00268 0.0009 0.6021 0.8972 1.500 0.2484 0.00767 0.00268 0.0012 0.5919 0.9012 1.750 0.2752 0.00769 0.00269 0.0015 0.5819 0.9060 2.000 0.3015 0.00773 0.00270 0.0019 0.5738 0.9115 2.250 0.3286 0.00776 0.00271 0.0022 0.5649 0.9155 2.500 0.3559 0.00780 0.00275 0.0024 0.5558 0.9201 2.750 0.3819 0.00786 0.00278 0.0028 0.5471 0.9255 3.000 0.4088 0.00788 0.00281 0.0031 0.5364 0.9301 3.250 0.4365 0.00794 0.00287 0.0032 0.5254 0.9343 3.500 0.4630 0.00801 0.00292 0.0035 0.5143 0.9395 3.750 0.4892 0.00807 0.00297 0.0038 0.5009 0.9447 4.000 0.5185 0.00817 0.00304 0.0035 0.4837 0.9485 4.250 0.5472 0.00828 0.00313 0.0033 0.4645 0.9530 4.500 0.5726 0.00842 0.00321 0.0038 0.4411 0.9589 4.750 0.6040 0.00867 0.00335 0.0028 0.4059 0.9618 5.000 0.6335 0.00908 0.00355 0.0021 0.3549 0.9655 5.250 0.6586 0.00961 0.00383 0.0022 0.3012 0.9711 5.500 0.6893 0.01018 0.00417 0.0010 0.2514 0.9741 5.750 0.7221 0.01076 0.00454 -0.0006 0.2113 0.9763 6.000 0.7540 0.01125 0.00489 -0.0020 0.1827 0.9793 6.250 0.7834 0.01167 0.00523 -0.0028 0.1646 0.9837 6.500 0.8171 0.01208 0.00558 -0.0046 0.1499 0.9860 6.750 0.8506 0.01251 0.00595 -0.0063 0.1383 0.9886 7.000 0.8837 0.01283 0.00628 -0.0078 0.1299 0.9917 7.250 0.9154 0.01327 0.00670 -0.0092 0.1222 0.9950 7.500 0.9498 0.01359 0.00704 -0.0111 0.1160 0.9976 7.750 0.9787 0.01411 0.00752 -0.0120 0.1094 1.0000 8.000 0.9891 0.01427 0.00774 -0.0089 0.1064 1.0000 8.250 0.9989 0.01452 0.00801 -0.0057 0.1031 1.0000 8.500 1.0091 0.01489 0.00837 -0.0027 0.0994 1.0000 8.750 1.0209 0.01534 0.00883 0.0000 0.0958 1.0000 9.000 1.0382 0.01560 0.00914 0.0017 0.0927 1.0000 9.250 1.0545 0.01594 0.00951 0.0036 0.0892 1.0000 9.500 1.0676 0.01651 0.01005 0.0059 0.0855 1.0000 9.750 1.0833 0.01695 0.01056 0.0077 0.0827 1.0000 10.000 1.1015 0.01728 0.01094 0.0091 0.0797 1.0000 10.250 1.1169 0.01772 0.01140 0.0109 0.0767 1.0000 10.500 1.1251 0.01840 0.01207 0.0139 0.0735 1.0000 10.750 1.1378 0.01892 0.01266 0.0160 0.0713 1.0000 11.000 1.1533 0.01933 0.01314 0.0177 0.0686 1.0000 11.250 1.1671 0.01986 0.01370 0.0194 0.0660 1.0000 11.500 1.1760 0.02068 0.01453 0.0216 0.0635 1.0000 11.750 1.1859 0.02153 0.01544 0.0235 0.0611 1.0000 12.000 1.2008 0.02210 0.01610 0.0248 0.0589 1.0000 12.250 1.2139 0.02281 0.01686 0.0260 0.0565 1.0000 12.500 1.2228 0.02383 0.01789 0.0275 0.0543 1.0000 12.750 1.2265 0.02530 0.01941 0.0293 0.0523 1.0000 13.000 1.2402 0.02612 0.02033 0.0301 0.0506 1.0000 13.250 1.2514 0.02715 0.02146 0.0310 0.0489 1.0000 13.500 1.2609 0.02836 0.02272 0.0318 0.0470 1.0000 13.750 1.2658 0.02998 0.02436 0.0326 0.0452 1.0000 14.000 1.2693 0.03181 0.02626 0.0335 0.0436 1.0000 14.250 1.2782 0.03325 0.02782 0.0340 0.0423 1.0000 14.500 1.2866 0.03476 0.02942 0.0343 0.0408 1.0000 14.750 1.2932 0.03647 0.03119 0.0345 0.0392 1.0000 15.000 1.2941 0.03878 0.03354 0.0347 0.0379 1.0000 15.250 1.2906 0.04155 0.03638 0.0349 0.0365 1.0000 15.500 1.2962 0.04355 0.03851 0.0348 0.0356 1.0000 15.750 1.3005 0.04571 0.04078 0.0346 0.0342 1.0000 16.000 1.3022 0.04821 0.04337 0.0342 0.0331 1.0000 16.250 1.3012 0.05108 0.04631 0.0337 0.0321 1.0000 16.500 1.2958 0.05455 0.04984 0.0328 0.0310 1.0000 16.750 1.2858 0.05861 0.05397 0.0319 0.0302 1.0000 17.000 1.2858 0.06178 0.05730 0.0308 0.0294 1.0000 17.250 1.2830 0.06537 0.06101 0.0295 0.0287 1.0000 17.500 1.2782 0.06935 0.06511 0.0279 0.0278 1.0000 17.750 1.2729 0.07353 0.06939 0.0261 0.0270 1.0000 18.000 1.2653 0.07815 0.07410 0.0240 0.0264 1.0000 18.250 1.2543 0.08337 0.07940 0.0216 0.0258 1.0000 18.500 1.2432 0.08872 0.08483 0.0191 0.0253 1.0000 18.750 1.2287 0.09471 0.09092 0.0162 0.0246 1.0000 19.000 1.2174 0.10052 0.09689 0.0132 0.0243 1.0000