XFOIL Version 6.96 Calculated polar for: EPPLER EA 6(-1)-009 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 ------ -------- --------- --------- -------- -------- -------- -11.750 -0.9218 0.06342 0.05978 -0.0143 1.0000 0.0197 -11.500 -0.9680 0.05453 0.05061 -0.0189 1.0000 0.0192 -11.250 -1.0043 0.04858 0.04436 -0.0187 1.0000 0.0191 -11.000 -1.0209 0.04453 0.04000 -0.0169 1.0000 0.0198 -10.750 -1.0314 0.03979 0.03481 -0.0154 1.0000 0.0210 -10.500 -1.0344 0.03505 0.02948 -0.0138 1.0000 0.0227 -10.250 -1.0252 0.03196 0.02596 -0.0127 1.0000 0.0242 -10.000 -1.0031 0.03206 0.02607 -0.0123 1.0000 0.0252 -9.750 -0.9813 0.03192 0.02586 -0.0120 1.0000 0.0265 -9.500 -0.9620 0.03079 0.02449 -0.0113 1.0000 0.0291 -9.250 -0.9440 0.02894 0.02220 -0.0106 1.0000 0.0317 -9.000 -0.9210 0.02881 0.02208 -0.0103 1.0000 0.0330 -8.750 -0.8984 0.02835 0.02151 -0.0100 1.0000 0.0347 -8.500 -0.8760 0.02759 0.02051 -0.0095 1.0000 0.0372 -8.250 -0.8529 0.02697 0.01956 -0.0090 1.0000 0.0391 -8.000 -0.8309 0.02540 0.01786 -0.0088 1.0000 0.0409 -7.750 -0.8072 0.02470 0.01711 -0.0086 1.0000 0.0427 -7.500 -0.7831 0.02397 0.01625 -0.0083 1.0000 0.0448 -7.250 -0.7586 0.02316 0.01528 -0.0080 1.0000 0.0472 -7.000 -0.7336 0.02224 0.01415 -0.0077 1.0000 0.0489 -6.750 -0.7082 0.02140 0.01313 -0.0073 1.0000 0.0500 -6.500 -0.6825 0.02073 0.01230 -0.0071 1.0000 0.0508 -6.250 -0.6572 0.01958 0.01110 -0.0069 1.0000 0.0518 -6.000 -0.6320 0.01866 0.01021 -0.0066 1.0000 0.0528 -5.750 -0.6066 0.01792 0.00947 -0.0064 1.0000 0.0538 -5.500 -0.5813 0.01726 0.00880 -0.0061 1.0000 0.0549 -5.250 -0.5560 0.01665 0.00819 -0.0059 1.0000 0.0560 -5.000 -0.5309 0.01612 0.00763 -0.0056 1.0000 0.0576 -4.750 -0.5061 0.01567 0.00715 -0.0052 1.0000 0.0593 -4.500 -0.4773 0.01522 0.00667 -0.0057 0.9885 0.0604 -4.250 -0.4446 0.01453 0.00602 -0.0071 0.9720 0.0615 -3.750 -0.3800 0.01356 0.00507 -0.0095 0.9487 0.0643 -3.500 -0.3492 0.01322 0.00470 -0.0102 0.9387 0.0659 -3.000 -0.2911 0.01267 0.00408 -0.0108 0.9206 0.0695 -2.750 -0.2633 0.01241 0.00380 -0.0107 0.9126 0.0721 -2.500 -0.2368 0.01220 0.00357 -0.0104 0.9031 0.0759 -2.250 -0.2108 0.01195 0.00335 -0.0100 0.8941 0.0831 -2.000 -0.1872 0.01132 0.00314 -0.0094 0.8851 0.1697 -1.750 -0.1623 0.01092 0.00297 -0.0089 0.8752 0.2299 -1.500 -0.1410 0.01009 0.00280 -0.0080 0.8631 0.3902 -1.250 -0.1195 0.00952 0.00270 -0.0066 0.8485 0.5019 -1.000 -0.0980 0.00915 0.00273 -0.0049 0.8316 0.6127 -0.750 -0.0742 0.00903 0.00276 -0.0035 0.8153 0.6649 -0.500 -0.0499 0.00897 0.00282 -0.0022 0.8005 0.7097 -0.250 -0.0254 0.00895 0.00286 -0.0010 0.7831 0.7454 0.000 0.0000 0.00895 0.00287 0.0000 0.7660 0.7660 0.250 0.0254 0.00895 0.00286 0.0010 0.7455 0.7832 0.500 0.0499 0.00897 0.00282 0.0022 0.7101 0.8004 0.750 0.0742 0.00903 0.00276 0.0035 0.6646 0.8152 1.000 0.0979 0.00916 0.00273 0.0049 0.6124 0.8316 1.250 0.1195 0.00952 0.00270 0.0066 0.5017 0.8485 1.500 0.1410 0.01009 0.00280 0.0080 0.3907 0.8630 1.750 0.1623 0.01092 0.00297 0.0089 0.2304 0.8753 2.000 0.1871 0.01131 0.00314 0.0094 0.1706 0.8851 2.250 0.2108 0.01195 0.00335 0.0100 0.0831 0.8941 2.500 0.2367 0.01220 0.00357 0.0104 0.0759 0.9032 2.750 0.2633 0.01241 0.00380 0.0108 0.0721 0.9126 3.000 0.2910 0.01267 0.00408 0.0108 0.0695 0.9206 3.500 0.3491 0.01322 0.00470 0.0102 0.0659 0.9387 3.750 0.3800 0.01356 0.00507 0.0095 0.0643 0.9487 4.250 0.4446 0.01453 0.00602 0.0071 0.0615 0.9718 4.500 0.4772 0.01522 0.00667 0.0057 0.0604 0.9883 4.750 0.5061 0.01567 0.00715 0.0052 0.0593 1.0000 5.000 0.5309 0.01613 0.00764 0.0056 0.0576 1.0000 5.250 0.5560 0.01664 0.00818 0.0059 0.0560 1.0000 5.500 0.5812 0.01726 0.00880 0.0062 0.0549 1.0000 5.750 0.6065 0.01792 0.00947 0.0064 0.0538 1.0000 6.000 0.6319 0.01865 0.01020 0.0067 0.0529 1.0000 6.250 0.6571 0.01957 0.01109 0.0069 0.0518 1.0000 6.500 0.6823 0.02072 0.01229 0.0071 0.0508 1.0000 6.750 0.7080 0.02140 0.01313 0.0074 0.0500 1.0000 7.000 0.7334 0.02223 0.01415 0.0077 0.0489 1.0000 7.250 0.7584 0.02315 0.01527 0.0081 0.0472 1.0000 7.500 0.7828 0.02396 0.01625 0.0084 0.0448 1.0000 7.750 0.8069 0.02469 0.01711 0.0086 0.0427 1.0000 8.000 0.8305 0.02539 0.01785 0.0088 0.0409 1.0000 8.250 0.8525 0.02696 0.01955 0.0091 0.0391 1.0000 8.500 0.8756 0.02757 0.02049 0.0096 0.0372 1.0000 8.750 0.8980 0.02833 0.02148 0.0101 0.0347 1.0000 9.000 0.9206 0.02879 0.02206 0.0104 0.0330 1.0000 9.250 0.9435 0.02893 0.02220 0.0107 0.0317 1.0000 9.500 0.9616 0.03076 0.02445 0.0114 0.0291 1.0000 9.750 0.9806 0.03194 0.02589 0.0121 0.0266 1.0000 10.000 1.0027 0.03198 0.02598 0.0125 0.0252 1.0000 10.250 1.0246 0.03194 0.02594 0.0128 0.0242 1.0000 10.500 1.0341 0.03494 0.02936 0.0139 0.0228 1.0000 10.750 1.0307 0.03978 0.03480 0.0155 0.0210 1.0000 11.000 1.0189 0.04472 0.04020 0.0171 0.0200 1.0000 11.250 1.0074 0.04816 0.04391 0.0187 0.0190 1.0000 11.500 0.9673 0.05456 0.05064 0.0190 0.0193 1.0000 11.750 0.9193 0.06378 0.06014 0.0141 0.0198 1.0000