XFOIL Version 6.94 Calculated polar for: AH 80-136 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 0.2100 0.01332 0.00815 -0.0147 0.5899 0.9959 0.500 0.2794 0.01346 0.00817 -0.0184 0.5852 1.0000 1.000 0.3311 0.01362 0.00824 -0.0185 0.5805 1.0000 1.500 0.3813 0.01361 0.00814 -0.0179 0.5757 1.0000 2.000 0.4305 0.01351 0.00789 -0.0168 0.5709 1.0000 2.500 0.4815 0.01425 0.00856 -0.0167 0.5648 1.0000 3.000 0.5344 0.01430 0.00864 -0.0167 0.5600 1.0000 3.500 0.5871 0.01458 0.00897 -0.0169 0.5539 1.0000 4.000 0.6391 0.01467 0.00911 -0.0165 0.5475 1.0000 4.500 0.6909 0.01451 0.00892 -0.0157 0.5420 1.0000 5.000 0.7427 0.01447 0.00884 -0.0148 0.5370 1.0000 5.500 0.7955 0.01489 0.00934 -0.0148 0.5297 1.0000 6.000 0.8498 0.01510 0.00979 -0.0153 0.5216 1.0000 6.500 0.9041 0.01467 0.00942 -0.0148 0.5126 1.0000 7.000 0.9586 0.01411 0.00885 -0.0139 0.5043 1.0000 7.500 1.0139 0.01399 0.00890 -0.0142 0.4911 1.0000 8.000 1.0702 0.01328 0.00831 -0.0139 0.4735 1.0000 8.500 1.1260 0.01315 0.00834 -0.0143 0.4473 1.0000 9.000 1.1794 0.01345 0.00853 -0.0148 0.4008 1.0000 9.500 1.2223 0.01569 0.01041 -0.0166 0.3098 1.0000 10.000 1.2353 0.02200 0.01619 -0.0219 0.1991 1.0000 10.500 1.2064 0.02926 0.02295 -0.0209 0.1220 1.0000 11.000 1.1831 0.03597 0.02925 -0.0194 0.0655 1.0000 11.500 1.1739 0.04158 0.03473 -0.0182 0.0404 1.0000 12.000 1.1670 0.04744 0.04060 -0.0174 0.0230 1.0000 13.000 1.1597 0.05957 0.05302 -0.0168 0.0144 1.0000 13.500 1.1619 0.06512 0.05870 -0.0168 0.0118 1.0000 14.000 1.1423 0.07288 0.06664 -0.0157 0.0096 1.0000 14.500 1.1511 0.07783 0.07184 -0.0155 0.0089 1.0000 15.000 1.1582 0.08278 0.07702 -0.0146 0.0085 1.0000 15.500 1.1624 0.08824 0.08279 -0.0137 0.0082 1.0000 16.000 1.1583 0.09513 0.09004 -0.0139 0.0082 1.0000 16.500 1.1467 0.10389 0.09918 -0.0156 0.0082 1.0000 17.000 1.1260 0.11495 0.11064 -0.0193 0.0083 1.0000 17.500 1.0997 0.12784 0.12391 -0.0250 0.0085 1.0000 18.000 1.0679 0.14292 0.13935 -0.0329 0.0086 1.0000 18.500 1.0328 0.16022 0.15697 -0.0429 0.0088 1.0000 19.000 0.9905 0.18147 0.17849 -0.0557 0.0091 1.0000