XFOIL Version 6.94 Calculated polar for: BL BAP 06 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1507 0.05085 0.04172 -0.0434 0.9998 0.2657 -2.750 -0.1108 0.04894 0.03933 -0.0467 0.9998 0.2453 -2.500 -0.0705 0.04785 0.03753 -0.0494 0.9998 0.2284 -2.250 -0.0402 0.04606 0.03573 -0.0504 0.9998 0.2232 -2.000 -0.0081 0.04479 0.03428 -0.0514 0.9998 0.2172 -1.750 0.0244 0.04384 0.03306 -0.0523 0.9998 0.2119 -1.500 0.0560 0.04314 0.03216 -0.0529 0.9998 0.2099 -1.250 0.0862 0.04252 0.03146 -0.0533 0.9998 0.2100 -1.000 0.1157 0.04199 0.03094 -0.0536 0.9998 0.2109 -0.750 0.2084 0.04041 0.02925 -0.0658 0.9702 0.2138 -0.500 0.2466 0.03652 0.02566 -0.0663 0.8144 0.2167 -0.250 0.5508 0.03209 0.01934 -0.1161 0.5791 0.4678 0.000 0.5860 0.03241 0.02007 -0.1154 0.5600 1.0002 0.250 0.6144 0.03328 0.02069 -0.1152 0.5466 1.0002 0.500 0.6361 0.03332 0.02074 -0.1139 0.5360 1.0002 0.750 0.6605 0.03343 0.02082 -0.1131 0.5254 1.0002 1.000 0.6903 0.03398 0.02123 -0.1136 0.5168 1.0002 1.250 0.7216 0.03471 0.02182 -0.1144 0.5099 1.0002 1.500 0.7538 0.03556 0.02249 -0.1153 0.5046 1.0002 1.750 0.7828 0.03642 0.02335 -0.1159 0.4997 1.0002 2.000 0.8113 0.03735 0.02426 -0.1163 0.4946 1.0002 2.250 0.8396 0.03830 0.02517 -0.1166 0.4896 1.0002 2.500 0.8680 0.03925 0.02606 -0.1169 0.4850 1.0002 2.750 0.8955 0.04038 0.02717 -0.1171 0.4813 1.0002 3.000 0.9211 0.04178 0.02868 -0.1174 0.4785 1.0002 3.250 0.9460 0.04324 0.03025 -0.1175 0.4756 1.0002 3.500 0.9695 0.04474 0.03184 -0.1173 0.4725 1.0002 3.750 0.9926 0.04626 0.03346 -0.1170 0.4692 1.0002 4.000 1.0158 0.04783 0.03509 -0.1167 0.4663 1.0002 4.250 1.0383 0.04962 0.03696 -0.1164 0.4644 1.0002 4.500 1.0612 0.05148 0.03887 -0.1162 0.4623 1.0002 4.750 1.0758 0.05390 0.04153 -0.1151 0.4608 1.0002 5.000 1.0869 0.05654 0.04440 -0.1138 0.4593 1.0002