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 = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1506 0.05186 0.04210 -0.0434 0.9998 0.2718 -2.750 -0.1079 0.05034 0.03987 -0.0474 0.9998 0.2528 -2.500 -0.0773 0.04836 0.03785 -0.0485 0.9998 0.2467 -2.250 -0.0444 0.04690 0.03616 -0.0499 0.9998 0.2398 -2.000 -0.0107 0.04580 0.03475 -0.0513 0.9998 0.2351 -1.750 0.0217 0.04496 0.03363 -0.0522 0.9998 0.2329 -1.500 0.0526 0.04422 0.03273 -0.0528 0.9998 0.2321 -1.250 0.0829 0.04361 0.03199 -0.0531 0.9998 0.2318 -1.000 0.1134 0.04314 0.03141 -0.0534 0.9998 0.2317 -0.750 0.1435 0.04276 0.03102 -0.0537 0.9998 0.2326 -0.500 0.1924 0.04231 0.03073 -0.0579 0.9918 0.2361 -0.250 0.2841 0.03690 0.02564 -0.0687 0.7647 0.2492 0.000 0.4729 0.02826 0.01762 -0.0931 0.6260 1.0002 0.250 0.6008 0.03200 0.01843 -0.1116 0.5936 1.0002 0.500 0.6466 0.03430 0.02050 -0.1158 0.5756 1.0002 0.750 0.6779 0.03584 0.02202 -0.1170 0.5622 1.0002 1.000 0.7066 0.03714 0.02331 -0.1175 0.5515 1.0002 1.250 0.7321 0.03798 0.02422 -0.1174 0.5434 1.0002 1.500 0.7574 0.03869 0.02500 -0.1173 0.5372 1.0002 1.750 0.7827 0.03936 0.02576 -0.1172 0.5318 1.0002 2.000 0.8090 0.04025 0.02670 -0.1173 0.5268 1.0002 2.250 0.8371 0.04138 0.02781 -0.1178 0.5219 1.0002 2.500 0.8618 0.04245 0.02898 -0.1178 0.5172 1.0002 2.750 0.8874 0.04369 0.03026 -0.1179 0.5124 1.0002 3.000 0.9140 0.04509 0.03165 -0.1182 0.5082 1.0002 3.250 0.9408 0.04666 0.03322 -0.1185 0.5053 1.0002 3.500 0.9639 0.04833 0.03497 -0.1185 0.5029 1.0002 3.750 0.9821 0.05010 0.03694 -0.1178 0.5003 1.0002 4.000 0.9987 0.05203 0.03903 -0.1169 0.4975 1.0002 4.250 1.0139 0.05416 0.04132 -0.1159 0.4952 1.0002 4.500 1.0264 0.05660 0.04392 -0.1148 0.4940 1.0002 4.750 1.0354 0.05929 0.04679 -0.1133 0.4930 1.0002 5.000 1.0402 0.06228 0.04997 -0.1114 0.4920 1.0002