XFOIL Version 6.94 Calculated polar for: EPPLER STF 863-615 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3580 0.02832 0.02295 -0.1055 0.8328 0.7317 0.500 0.4154 0.02810 0.02282 -0.1047 0.8298 0.7455 1.000 0.4905 0.02791 0.02262 -0.1095 0.8282 0.7470 2.500 0.6443 0.02766 0.02252 -0.1109 0.7979 0.7517 3.000 0.7188 0.02681 0.02179 -0.1149 0.7944 0.7529 3.500 0.7883 0.02585 0.02099 -0.1178 0.7884 0.7543 4.000 0.8712 0.02253 0.01786 -0.1213 0.7757 0.7552 4.500 0.9199 0.02028 0.01579 -0.1188 0.7428 0.7563 5.000 0.9792 0.01727 0.01121 -0.1158 0.4695 0.7573 5.500 0.9459 0.02155 0.01407 -0.1022 0.2204 0.7583 6.000 0.9431 0.02514 0.01652 -0.0941 0.0329 0.7594 6.500 0.9747 0.02664 0.01813 -0.0912 0.0267 0.7613 7.000 1.0043 0.02831 0.01988 -0.0883 0.0225 0.7626 7.500 1.0315 0.03015 0.02178 -0.0853 0.0189 0.7639 8.000 1.0566 0.03223 0.02400 -0.0818 0.0178 0.7653 8.500 1.0827 0.03433 0.02623 -0.0786 0.0169 0.7667 9.000 1.1113 0.03650 0.02849 -0.0758 0.0161 0.7683 9.500 1.1400 0.03852 0.03060 -0.0736 0.0132 0.7700 10.000 1.1691 0.04056 0.03297 -0.0712 0.0116 0.7718 10.500 1.1979 0.04313 0.03573 -0.0688 0.0103 0.7735 11.000 1.2182 0.04584 0.03880 -0.0658 0.0084 0.7752 11.500 1.2322 0.04968 0.04318 -0.0620 0.0061 0.7769 12.000 1.2296 0.05734 0.05183 -0.0558 0.0047 0.7787 12.500 1.2083 0.06532 0.06050 -0.0500 0.0044 0.7807 13.000 1.1716 0.07502 0.07084 -0.0454 0.0044 0.7827 13.500 1.1204 0.08776 0.08419 -0.0435 0.0045 0.7842 14.000 1.0726 0.10187 0.09876 -0.0464 0.0047 0.7855 14.500 1.0282 0.11843 0.11569 -0.0543 0.0049 0.7868 15.000 0.9906 0.13810 0.13564 -0.0670 0.0052 0.7880 15.500 0.9657 0.15900 0.15662 -0.0798 0.0056 0.7892 16.500 0.6683 0.16833 0.16595 -0.0592 0.0137 0.7824 17.000 0.6647 0.17598 0.17362 -0.0610 0.0186 0.7845 17.500 0.6531 0.18589 0.18349 -0.0657 0.0172 0.7860 18.000 0.6625 0.18929 0.18695 -0.0663 0.0158 0.7887 18.500 0.6556 0.19802 0.19565 -0.0704 0.0155 0.7905 19.000 0.6554 0.20487 0.20250 -0.0733 0.0141 0.7928 19.500 0.6612 0.20978 0.20744 -0.0751 0.0133 0.7956