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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.5363 0.08444 0.08075 -0.0299 1.0000 0.0130 -10.250 -0.5581 0.07324 0.06956 -0.0385 1.0000 0.0127 -10.000 -0.5830 0.06549 0.06170 -0.0433 1.0000 0.0124 -9.750 -0.6087 0.05983 0.05590 -0.0445 1.0000 0.0121 -9.500 -0.6379 0.05477 0.05066 -0.0427 1.0000 0.0119 -9.250 -0.6648 0.05046 0.04615 -0.0385 1.0000 0.0118 -9.000 -0.7088 0.04187 0.03681 -0.0320 1.0000 0.0111 -8.750 -0.7161 0.03827 0.03277 -0.0279 1.0000 0.0110 -8.500 -0.7158 0.03547 0.02960 -0.0244 1.0000 0.0109 -8.250 -0.7111 0.03314 0.02698 -0.0214 1.0000 0.0109 -8.000 -0.7035 0.03099 0.02454 -0.0185 1.0000 0.0110 -7.750 -0.6935 0.02915 0.02246 -0.0159 1.0000 0.0110 -7.500 -0.6819 0.02751 0.02061 -0.0134 1.0000 0.0111 -7.250 -0.6582 0.02584 0.01874 -0.0133 0.9958 0.0114 -7.000 -0.6266 0.02411 0.01679 -0.0147 0.9875 0.0116 -6.750 -0.5953 0.02264 0.01514 -0.0158 0.9771 0.0120 -6.500 -0.5637 0.02131 0.01364 -0.0168 0.9653 0.0124 -6.250 -0.5317 0.02006 0.01226 -0.0179 0.9518 0.0129 -6.000 -0.4984 0.01891 0.01097 -0.0192 0.9374 0.0135 -5.750 -0.4645 0.01786 0.00984 -0.0207 0.9221 0.0145 -5.500 -0.4302 0.01712 0.00905 -0.0223 0.9054 0.0159 -5.250 -0.3986 0.01642 0.00826 -0.0232 0.8874 0.0183 -5.000 -0.3699 0.01580 0.00754 -0.0234 0.8686 0.0204 -4.750 -0.3441 0.01521 0.00685 -0.0230 0.8506 0.0230 -4.500 -0.3198 0.01473 0.00630 -0.0223 0.8335 0.0286 -4.000 -0.2737 0.01382 0.00536 -0.0203 0.8030 0.0542 -3.750 -0.2513 0.01338 0.00499 -0.0193 0.7892 0.0814 -3.500 -0.2303 0.01282 0.00464 -0.0182 0.7766 0.1344 -3.250 -0.2125 0.01202 0.00428 -0.0166 0.7650 0.2432 -3.000 -0.1988 0.01104 0.00393 -0.0143 0.7541 0.4025 -2.750 -0.1866 0.01017 0.00380 -0.0112 0.7432 0.5779 -2.500 -0.1657 0.00995 0.00389 -0.0092 0.7337 0.6791 -2.250 -0.1411 0.00996 0.00394 -0.0080 0.7243 0.7281 -2.000 -0.1160 0.01003 0.00398 -0.0069 0.7153 0.7604 -1.750 -0.0912 0.01015 0.00406 -0.0057 0.7070 0.7898 -1.500 -0.0672 0.01030 0.00418 -0.0043 0.6984 0.8171 -1.250 -0.0415 0.01046 0.00428 -0.0032 0.6908 0.8347 -1.000 -0.0158 0.01056 0.00431 -0.0024 0.6828 0.8474 -0.750 0.0122 0.01065 0.00432 -0.0020 0.6755 0.8550 -0.500 0.0376 0.01068 0.00428 -0.0014 0.6681 0.8636 -0.250 0.0661 0.01073 0.00426 -0.0013 0.6609 0.8685 0.000 0.0938 0.01078 0.00423 -0.0012 0.6540 0.8738 0.250 0.1189 0.01079 0.00418 -0.0006 0.6468 0.8804 0.500 0.1482 0.01085 0.00418 -0.0007 0.6405 0.8841 0.750 0.1765 0.01089 0.00419 -0.0007 0.6330 0.8886 1.000 0.2027 0.01093 0.00417 -0.0003 0.6265 0.8944 1.250 0.2306 0.01097 0.00419 -0.0003 0.6181 0.8987 1.500 0.2596 0.01103 0.00419 -0.0004 0.6092 0.9027 1.750 0.2866 0.01106 0.00419 -0.0002 0.5974 0.9078 2.000 0.3123 0.01108 0.00417 0.0003 0.5842 0.9132 2.250 0.3420 0.01114 0.00418 0.0000 0.5700 0.9167 2.500 0.3706 0.01119 0.00420 -0.0001 0.5566 0.9211 2.750 0.3960 0.01124 0.00422 0.0004 0.5443 0.9270 3.000 0.4262 0.01132 0.00427 -0.0001 0.5315 0.9305 3.250 0.4568 0.01140 0.00434 -0.0007 0.5173 0.9341 3.500 0.4854 0.01148 0.00441 -0.0009 0.5022 0.9389 3.750 0.5122 0.01157 0.00449 -0.0007 0.4856 0.9442 4.000 0.5441 0.01169 0.00459 -0.0017 0.4644 0.9473 4.250 0.5738 0.01186 0.00468 -0.0022 0.4375 0.9513 4.500 0.5998 0.01206 0.00480 -0.0020 0.4057 0.9572 4.750 0.6287 0.01240 0.00497 -0.0026 0.3629 0.9610 5.000 0.6568 0.01288 0.00522 -0.0032 0.3124 0.9651 5.250 0.6821 0.01342 0.00556 -0.0033 0.2694 0.9710 5.500 0.7114 0.01395 0.00593 -0.0042 0.2351 0.9749 5.750 0.7407 0.01447 0.00633 -0.0052 0.2072 0.9791 6.000 0.7682 0.01495 0.00674 -0.0057 0.1860 0.9845 6.250 0.7993 0.01543 0.00716 -0.0070 0.1694 0.9883 6.500 0.8289 0.01589 0.00759 -0.0080 0.1567 0.9931 6.750 0.8591 0.01636 0.00806 -0.0092 0.1457 0.9977 7.250 0.8918 0.01715 0.00886 -0.0058 0.1322 1.0000 7.500 0.9035 0.01754 0.00926 -0.0031 0.1265 1.0000 7.750 0.9158 0.01798 0.00969 -0.0006 0.1218 1.0000 8.000 0.9301 0.01837 0.01012 0.0015 0.1167 1.0000 8.250 0.9434 0.01885 0.01060 0.0038 0.1122 1.0000 8.500 0.9572 0.01936 0.01113 0.0059 0.1082 1.0000 8.750 0.9730 0.01981 0.01165 0.0078 0.1040 1.0000 9.000 0.9876 0.02034 0.01220 0.0096 0.1002 1.0000 9.250 0.9999 0.02101 0.01285 0.0118 0.0967 1.0000 9.500 1.0159 0.02149 0.01344 0.0134 0.0932 1.0000 9.750 1.0293 0.02203 0.01406 0.0154 0.0899 1.0000 10.000 1.0407 0.02266 0.01472 0.0176 0.0868 1.0000 10.250 1.0501 0.02346 0.01551 0.0199 0.0841 1.0000 10.500 1.0641 0.02409 0.01626 0.0216 0.0813 1.0000 10.750 1.0770 0.02479 0.01706 0.0232 0.0782 1.0000 11.000 1.0884 0.02559 0.01792 0.0248 0.0754 1.0000 11.250 1.0973 0.02661 0.01895 0.0265 0.0730 1.0000 11.500 1.1094 0.02752 0.01997 0.0278 0.0706 1.0000 11.750 1.1210 0.02847 0.02104 0.0290 0.0680 1.0000 12.000 1.1313 0.02952 0.02218 0.0301 0.0656 1.0000 12.250 1.1395 0.03075 0.02347 0.0312 0.0634 1.0000 12.500 1.1470 0.03215 0.02491 0.0322 0.0615 1.0000 12.750 1.1571 0.03340 0.02632 0.0330 0.0594 1.0000 13.000 1.1658 0.03478 0.02783 0.0337 0.0571 1.0000 13.250 1.1729 0.03631 0.02944 0.0343 0.0552 1.0000 13.500 1.1777 0.03807 0.03125 0.0348 0.0534 1.0000 13.750 1.1826 0.03994 0.03320 0.0352 0.0517 1.0000 14.000 1.1888 0.04175 0.03519 0.0355 0.0499 1.0000 14.250 1.1933 0.04376 0.03733 0.0356 0.0481 1.0000 14.500 1.1965 0.04594 0.03962 0.0356 0.0466 1.0000 14.750 1.1975 0.04836 0.04212 0.0353 0.0452 1.0000 15.000 1.1963 0.05111 0.04491 0.0350 0.0440 1.0000 15.250 1.1975 0.05375 0.04774 0.0346 0.0427 1.0000 15.500 1.1971 0.05664 0.05080 0.0340 0.0413 1.0000 15.750 1.1950 0.05981 0.05411 0.0331 0.0401 1.0000 16.000 1.1917 0.06325 0.05768 0.0319 0.0390 1.0000 16.250 1.1871 0.06700 0.06153 0.0305 0.0380 1.0000 16.500 1.1811 0.07106 0.06569 0.0289 0.0372 1.0000 16.750 1.1740 0.07542 0.07014 0.0270 0.0364 1.0000 17.000 1.1656 0.08024 0.07516 0.0248 0.0356 1.0000 17.250 1.1554 0.08554 0.08064 0.0223 0.0349 1.0000 17.500 1.1432 0.09137 0.08665 0.0193 0.0342 1.0000 17.750 1.1290 0.09774 0.09317 0.0159 0.0335 1.0000 18.000 1.1136 0.10458 0.10018 0.0121 0.0330 1.0000 18.250 1.0959 0.11213 0.10787 0.0078 0.0324 1.0000 18.500 1.0749 0.12050 0.11639 0.0030 0.0322 1.0000 18.750 1.0493 0.13023 0.12627 -0.0027 0.0319 1.0000