XFOIL Version 6.94 Calculated polar for: HOBIE 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 0.4599 0.00898 0.00228 -0.1027 0.7560 0.3269 0.500 0.5116 0.00859 0.00235 -0.1017 0.7318 0.4969 1.000 0.5704 0.00763 0.00238 -0.1016 0.7060 1.0000 1.500 0.6231 0.00782 0.00242 -0.1006 0.6764 1.0000 2.000 0.6749 0.00806 0.00249 -0.0994 0.6394 1.0000 2.500 0.7259 0.00837 0.00260 -0.0981 0.5973 1.0000 3.000 0.7771 0.00875 0.00281 -0.0969 0.5586 1.0000 3.500 0.8282 0.00918 0.00312 -0.0958 0.5253 1.0000 4.000 0.8795 0.00962 0.00350 -0.0947 0.4951 1.0000 4.500 0.9298 0.01010 0.00392 -0.0935 0.4605 1.0000 5.000 0.9787 0.01068 0.00442 -0.0921 0.4238 1.0000 5.500 1.0263 0.01134 0.00499 -0.0905 0.3703 1.0000 6.000 1.0671 0.01254 0.00572 -0.0881 0.2577 1.0000 6.500 1.1055 0.01415 0.00698 -0.0854 0.1888 1.0000 7.000 1.1331 0.01691 0.00905 -0.0813 0.0589 1.0000 7.500 1.1640 0.01916 0.01136 -0.0772 0.0370 1.0000 8.000 1.1979 0.02089 0.01324 -0.0737 0.0293 1.0000 8.500 1.2138 0.02417 0.01672 -0.0676 0.0244 1.0000 9.000 1.2386 0.02651 0.01925 -0.0629 0.0221 1.0000 9.500 1.2630 0.02921 0.02211 -0.0586 0.0202 1.0000 10.000 1.2941 0.03485 0.02798 -0.0563 0.0178 1.0000 10.500 1.3176 0.03844 0.03197 -0.0523 0.0172 1.0000 11.000 1.3323 0.04389 0.03793 -0.0480 0.0168 1.0000 11.500 1.3278 0.05039 0.04499 -0.0429 0.0168 1.0000 12.000 1.3082 0.05765 0.05275 -0.0387 0.0168 1.0000 12.500 1.2817 0.06547 0.06103 -0.0367 0.0166 1.0000 13.000 1.2465 0.07571 0.07169 -0.0378 0.0169 1.0000 13.500 1.2065 0.08801 0.08437 -0.0421 0.0171 1.0000 14.000 0.9901 0.09619 0.09329 -0.0466 0.0183 1.0000 14.500 0.9022 0.12190 0.11958 -0.0655 0.0203 1.0000