XFOIL Version 6.94 Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) AIRF 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 0.2034 0.00675 0.00211 -0.0299 0.6645 0.9783 0.500 0.2485 0.00684 0.00180 -0.0283 0.6498 0.8937 1.000 0.3523 0.00704 0.00203 -0.0380 0.6230 1.0000 1.500 0.4039 0.00713 0.00200 -0.0372 0.6014 1.0000 2.000 0.4548 0.00727 0.00195 -0.0361 0.5627 1.0000 2.500 0.5063 0.00746 0.00199 -0.0352 0.5210 1.0000 3.000 0.5525 0.00832 0.00206 -0.0336 0.3860 1.0000 3.500 0.6053 0.00856 0.00230 -0.0330 0.3791 1.0000 4.000 0.6586 0.00884 0.00264 -0.0325 0.3738 1.0000 4.500 0.7116 0.00922 0.00294 -0.0321 0.3545 1.0000 5.000 0.7647 0.00961 0.00336 -0.0317 0.3378 1.0000 5.500 0.8178 0.01003 0.00375 -0.0314 0.3162 1.0000 6.000 0.8710 0.01043 0.00416 -0.0312 0.2949 1.0000 6.500 0.9238 0.01092 0.00461 -0.0308 0.2623 1.0000 7.000 0.9758 0.01147 0.00512 -0.0304 0.2317 1.0000 7.500 1.0255 0.01230 0.00578 -0.0299 0.1768 1.0000 8.000 1.0676 0.01411 0.00710 -0.0284 0.0852 1.0000 8.500 1.1052 0.01641 0.00913 -0.0263 0.0419 1.0000 9.000 1.1474 0.01794 0.01072 -0.0246 0.0330 1.0000 9.500 1.1868 0.01959 0.01252 -0.0226 0.0301 1.0000 10.000 1.2217 0.02146 0.01452 -0.0201 0.0278 1.0000 10.500 1.2535 0.02335 0.01654 -0.0175 0.0242 1.0000 11.000 1.2790 0.02547 0.01882 -0.0141 0.0220 1.0000 11.500 1.2892 0.02819 0.02175 -0.0090 0.0204 1.0000 12.000 1.2999 0.03142 0.02515 -0.0055 0.0191 1.0000 12.500 1.3090 0.03532 0.02918 -0.0035 0.0184 1.0000 13.000 1.3159 0.03996 0.03414 -0.0021 0.0174 1.0000 13.500 1.3218 0.04500 0.03943 -0.0005 0.0173 1.0000 14.000 1.3254 0.05037 0.04509 -0.0004 0.0168 1.0000 14.500 1.3253 0.05630 0.05123 -0.0014 0.0161 1.0000 15.000 1.3177 0.06357 0.05882 -0.0018 0.0160 1.0000 15.500 1.3134 0.07027 0.06563 -0.0030 0.0154 1.0000 16.000 1.2955 0.07955 0.07525 -0.0058 0.0154 1.0000 16.500 1.2651 0.09185 0.08795 -0.0121 0.0152 1.0000 18.000 1.1631 0.13710 0.13420 -0.0379 0.0152 1.0000