XFOIL Version 6.94 Calculated polar for: EPPLER 67 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5289 0.00716 0.00256 -0.1293 0.8024 0.7490 0.500 0.5818 0.00714 0.00259 -0.1283 0.7857 0.7990 1.000 0.6318 0.00714 0.00265 -0.1266 0.7677 0.8461 1.500 0.6776 0.00716 0.00271 -0.1239 0.7483 0.8932 2.000 0.7195 0.00714 0.00272 -0.1203 0.7271 0.9477 2.500 0.7850 0.00721 0.00276 -0.1224 0.7032 1.0000 3.000 0.8367 0.00742 0.00288 -0.1217 0.6773 1.0000 3.500 0.8871 0.00771 0.00306 -0.1206 0.6490 1.0000 4.000 0.9356 0.00800 0.00329 -0.1191 0.6176 1.0000 4.500 0.9818 0.00840 0.00358 -0.1172 0.5824 1.0000 5.000 1.0253 0.00886 0.00393 -0.1147 0.5420 1.0000 5.500 1.0658 0.00942 0.00436 -0.1117 0.4945 1.0000 6.000 1.1010 0.01015 0.00489 -0.1077 0.4394 1.0000 6.500 1.1302 0.01102 0.00552 -0.1027 0.3773 1.0000 7.000 1.1528 0.01221 0.00635 -0.0967 0.3017 1.0000 7.500 1.1755 0.01357 0.00736 -0.0910 0.2285 1.0000 8.000 1.2003 0.01495 0.00847 -0.0860 0.1716 1.0000 8.500 1.2246 0.01642 0.00971 -0.0811 0.1244 1.0000 9.000 1.2478 0.01798 0.01110 -0.0763 0.0862 1.0000 9.500 1.2672 0.01983 0.01279 -0.0712 0.0530 1.0000 10.000 1.2796 0.02224 0.01507 -0.0654 0.0295 1.0000 10.500 1.2950 0.02456 0.01743 -0.0605 0.0231 1.0000 11.000 1.3097 0.02703 0.02002 -0.0560 0.0200 1.0000 11.500 1.3261 0.02954 0.02268 -0.0522 0.0178 1.0000 12.000 1.3340 0.03286 0.02618 -0.0481 0.0165 1.0000 12.500 1.3448 0.03620 0.02967 -0.0449 0.0150 1.0000 13.000 1.3489 0.04040 0.03406 -0.0420 0.0139 1.0000 13.500 1.3582 0.04441 0.03826 -0.0400 0.0126 1.0000 14.000 1.3560 0.04998 0.04397 -0.0383 0.0118 1.0000 14.500 1.3610 0.05521 0.04949 -0.0375 0.0110 1.0000 15.000 1.3617 0.06127 0.05577 -0.0375 0.0102 1.0000 15.500 1.3557 0.06867 0.06334 -0.0381 0.0095 1.0000 16.000 1.3513 0.07646 0.07150 -0.0398 0.0088 1.0000 16.500 1.3437 0.08521 0.08052 -0.0426 0.0082 1.0000 17.000 1.3339 0.09464 0.09013 -0.0461 0.0077 1.0000 17.500 1.3149 0.10646 0.10233 -0.0513 0.0073 1.0000 18.000 1.2948 0.11916 0.11542 -0.0579 0.0070 1.0000 18.500 1.2731 0.13272 0.12933 -0.0657 0.0067 1.0000 19.000 1.2496 0.14713 0.14407 -0.0746 0.0066 1.0000 19.500 1.2229 0.16296 0.16022 -0.0849 0.0066 1.0000 20.000 1.1885 0.18167 0.17925 -0.0972 0.0067 1.0000 20.500 1.1357 0.20798 0.20587 -0.1137 0.0072 1.0000