XFOIL Version 6.96 Calculated polar for: EPPLER 547 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.3919 0.10362 0.09898 -0.0498 1.0000 0.1397 -10.750 -0.3977 0.09980 0.09523 -0.0508 1.0000 0.1452 -10.500 -0.4291 0.09365 0.08923 -0.0546 1.0000 0.1520 -10.250 -0.4163 0.09122 0.08683 -0.0525 1.0000 0.1559 -10.000 -0.4873 0.08482 0.08057 -0.0574 1.0000 0.1635 -8.500 -0.7179 0.05776 0.05182 -0.0382 0.9764 0.0664 -8.250 -0.6943 0.05163 0.04492 -0.0387 0.9697 0.0530 -8.000 -0.6736 0.04726 0.04028 -0.0394 0.9611 0.0517 -7.750 -0.6456 0.04304 0.03563 -0.0407 0.9549 0.0496 -7.500 -0.6185 0.03960 0.03166 -0.0410 0.9467 0.0479 -7.250 -0.5753 0.03633 0.02791 -0.0437 0.9426 0.0476 -7.000 -0.5422 0.03419 0.02553 -0.0443 0.9344 0.0491 -6.750 -0.4957 0.03248 0.02346 -0.0473 0.9296 0.0536 -6.500 -0.4381 0.02985 0.02101 -0.0520 0.9280 0.0617 -6.250 -0.4019 0.02832 0.01960 -0.0533 0.9209 0.0737 -6.000 -0.3665 0.02650 0.01802 -0.0548 0.9151 0.0985 -5.750 -0.3538 0.02475 0.01679 -0.0529 0.9056 0.1550 -5.500 -0.3702 0.02201 0.01548 -0.0476 0.8945 0.3433 -5.000 -0.1486 0.03444 0.02846 -0.0520 0.8991 0.7212 -4.750 -0.0719 0.03529 0.02896 -0.0577 0.8969 0.7470 -4.500 0.0016 0.03589 0.02931 -0.0628 0.8921 0.7748 -4.250 0.0714 0.03549 0.02867 -0.0686 0.8860 0.7972 -4.000 0.2244 0.03403 0.02693 -0.0849 0.8875 0.9044 -3.750 0.2770 0.03264 0.02535 -0.0905 0.8791 0.9308 -3.500 0.3211 0.03125 0.02382 -0.0948 0.8675 0.9493 -3.250 0.3601 0.03037 0.02281 -0.0983 0.8566 0.9694 -2.500 0.4769 0.02635 0.01847 -0.1093 0.8251 1.0000 -2.250 0.4959 0.02610 0.01811 -0.1087 0.8160 1.0000 -2.000 0.5122 0.02598 0.01795 -0.1078 0.8057 1.0000 -1.750 0.5295 0.02587 0.01779 -0.1070 0.7970 1.0000 -1.500 0.5476 0.02573 0.01759 -0.1063 0.7884 1.0000 -1.250 0.5641 0.02570 0.01754 -0.1053 0.7796 1.0000 -1.000 0.5829 0.02558 0.01736 -0.1046 0.7722 1.0000 -0.750 0.5991 0.02565 0.01744 -0.1036 0.7639 1.0000 -0.500 0.6180 0.02557 0.01731 -0.1028 0.7568 1.0000 -0.250 0.5124 0.02958 0.02136 -0.0784 0.7487 0.9409 0.000 0.5282 0.02939 0.02115 -0.0772 0.7420 0.9364 0.250 0.5153 0.03012 0.02188 -0.0709 0.7350 0.9270 0.500 0.5312 0.03005 0.02182 -0.0698 0.7280 0.9252 0.750 0.5514 0.02985 0.02155 -0.0689 0.7232 0.9249 1.000 0.5556 0.03027 0.02205 -0.0660 0.7147 0.9227 1.250 0.5735 0.03015 0.02191 -0.0649 0.7096 0.9224 1.500 0.5775 0.03060 0.02242 -0.0618 0.7023 0.9212 1.750 0.5885 0.03068 0.02251 -0.0596 0.6962 0.9201 2.000 0.6114 0.03045 0.02224 -0.0591 0.6923 0.9208 2.250 0.5989 0.03138 0.02329 -0.0535 0.6833 0.9193 2.500 0.6180 0.03120 0.02311 -0.0523 0.6787 0.9194 2.750 0.6098 0.03204 0.02403 -0.0473 0.6710 0.9195 3.000 0.6162 0.03222 0.02424 -0.0443 0.6652 0.9194 3.250 0.6443 0.03176 0.02376 -0.0445 0.6617 0.9199 3.500 0.6032 0.03344 0.02556 -0.0345 0.6515 0.9208 3.750 0.6296 0.03300 0.02512 -0.0343 0.6477 0.9216 4.000 0.5376 0.03530 0.02749 -0.0162 0.6363 0.9235 4.250 0.4331 0.03681 0.02898 0.0040 0.6268 0.9288 4.500 0.6010 0.03395 0.02615 -0.0168 0.6302 0.9266 4.750 0.4284 0.03819 0.03042 0.0108 0.6124 0.9345 5.000 0.5554 0.03562 0.02792 -0.0026 0.6143 0.9320 5.250 0.4590 0.03829 0.03058 0.0137 0.6007 0.9409 5.500 0.5486 0.03664 0.02902 0.0055 0.5999 0.9398 5.750 0.4561 0.04108 0.03350 0.0176 0.5822 0.9483 6.000 0.5465 0.03822 0.03071 0.0116 0.5836 0.9471 6.250 0.4508 0.04458 0.03711 0.0203 0.5606 0.9583 6.500 0.5009 0.04375 0.03637 0.0178 0.5565 0.9600 6.750 0.5656 0.04169 0.03442 0.0148 0.5549 0.9609 7.000 0.6388 0.03913 0.03198 0.0111 0.5543 0.9610 7.250 0.7381 0.03597 0.02895 0.0035 0.5537 0.9590 7.500 0.7031 0.03872 0.03179 0.0090 0.5396 0.9675 7.750 0.8200 0.03485 0.02807 -0.0006 0.5387 0.9635 8.000 0.7925 0.03703 0.03038 0.0046 0.5254 0.9722 8.250 0.9216 0.03256 0.02602 -0.0066 0.5229 0.9671 8.500 0.9246 0.03340 0.02703 -0.0044 0.5105 0.9730 8.750 0.9608 0.03296 0.02676 -0.0060 0.4991 0.9767 9.000 1.0256 0.03103 0.02492 -0.0105 0.4881 0.9776 9.250 1.0794 0.02956 0.02354 -0.0138 0.4751 0.9800 9.500 1.1163 0.02880 0.02288 -0.0153 0.4602 0.9842 9.750 1.1428 0.02845 0.02267 -0.0157 0.4433 0.9902 10.000 1.1635 0.02823 0.02258 -0.0153 0.4253 0.9983 10.250 1.1565 0.02784 0.02219 -0.0097 0.4140 1.0000 10.500 1.1205 0.02802 0.02239 -0.0004 0.4066 1.0000 10.750 1.1266 0.02795 0.02234 0.0021 0.3897 1.0000 11.000 1.1354 0.02813 0.02249 0.0039 0.3700 1.0000 11.250 1.1344 0.02908 0.02348 0.0061 0.3492 1.0000 11.500 1.1407 0.02986 0.02412 0.0076 0.3262 1.0000 11.750 1.1374 0.03145 0.02567 0.0094 0.3033 1.0000 12.000 1.1375 0.03302 0.02707 0.0109 0.2802 1.0000 12.250 1.1337 0.03504 0.02900 0.0123 0.2582 1.0000 12.500 1.1322 0.03703 0.03078 0.0136 0.2372 1.0000 12.750 1.1274 0.03942 0.03314 0.0147 0.2177 1.0000 13.000 1.1237 0.04183 0.03545 0.0157 0.1995 1.0000 13.250 1.1211 0.04424 0.03773 0.0165 0.1827 1.0000 13.500 1.1198 0.04666 0.04001 0.0172 0.1670 1.0000 13.750 1.1188 0.04915 0.04239 0.0178 0.1523 1.0000 14.000 1.1169 0.05183 0.04504 0.0182 0.1391 1.0000 14.250 1.1153 0.05459 0.04782 0.0184 0.1272 1.0000 14.500 1.1158 0.05728 0.05051 0.0187 0.1162 1.0000 14.750 1.1191 0.05979 0.05300 0.0189 0.1062 1.0000 15.000 1.1259 0.06202 0.05510 0.0191 0.0967 1.0000 15.250 1.1246 0.06511 0.05837 0.0190 0.0897 1.0000 15.500 1.1314 0.06755 0.06080 0.0191 0.0825 1.0000 15.750 1.1311 0.07061 0.06396 0.0188 0.0769 1.0000 16.000 1.1400 0.07309 0.06645 0.0190 0.0711 1.0000 16.250 1.1342 0.07690 0.07049 0.0182 0.0671 1.0000 16.500 1.1496 0.07882 0.07224 0.0185 0.0614 1.0000 16.750 1.1378 0.08342 0.07717 0.0174 0.0595 1.0000 17.000 1.1280 0.08800 0.08200 0.0161 0.0571 1.0000 17.250 1.1235 0.09194 0.08607 0.0148 0.0544 1.0000 17.500 1.1318 0.09493 0.08900 0.0146 0.0510 1.0000 17.750 1.1122 0.10099 0.09537 0.0122 0.0504 1.0000 18.000 1.0916 0.10762 0.10229 0.0092 0.0498 1.0000 18.250 1.0692 0.11485 0.10978 0.0056 0.0495 1.0000 18.500 1.0447 0.12286 0.11804 0.0013 0.0496 1.0000 18.750 1.0175 0.13188 0.12727 -0.0038 0.0501 1.0000