XFOIL Version 6.94 Calculated polar for: BL BAP 04 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 -0.0540 0.04721 0.03857 -0.0644 0.9521 0.2574 -2.750 -0.0100 0.04461 0.03574 -0.0682 0.9386 0.2469 -2.500 0.0359 0.04295 0.03356 -0.0719 0.9256 0.2367 -2.250 0.0748 0.04152 0.03193 -0.0741 0.9092 0.2327 -2.000 0.0945 0.04012 0.03053 -0.0727 0.8811 0.2310 -1.750 0.0868 0.03988 0.03045 -0.0669 0.8062 0.2301 -1.500 0.1442 0.03814 0.02837 -0.0722 0.7699 0.2287 -1.250 0.2128 0.03622 0.02597 -0.0791 0.7550 0.2301 -1.000 0.2820 0.03426 0.02365 -0.0862 0.7458 0.2379 -0.750 0.3463 0.03272 0.02200 -0.0929 0.7415 0.2520 -0.500 0.3985 0.03207 0.02128 -0.0979 0.7441 0.2667 -0.250 0.4478 0.03139 0.02078 -0.1028 0.7461 0.2966 0.000 0.4855 0.02830 0.01998 -0.1042 0.7434 1.0002 0.250 0.5417 0.02862 0.01916 -0.1087 0.7387 1.0002 0.750 0.6299 0.02993 0.01948 -0.1159 0.7235 1.0002 1.000 0.6758 0.03067 0.01980 -0.1197 0.7134 1.0002 1.250 0.7074 0.03185 0.02084 -0.1214 0.7059 1.0002 1.500 0.7381 0.03315 0.02205 -0.1231 0.6994 1.0002 1.750 0.7746 0.03441 0.02315 -0.1255 0.6920 1.0002 2.000 0.8018 0.03601 0.02470 -0.1265 0.6850 1.0002 2.250 0.8260 0.03771 0.02638 -0.1269 0.6762 1.0002 2.500 0.8573 0.03933 0.02788 -0.1282 0.6659 1.0002 2.750 0.8776 0.04126 0.02981 -0.1279 0.6559 1.0002 3.000 0.9017 0.04324 0.03178 -0.1281 0.6471 1.0002 3.250 0.9196 0.04545 0.03400 -0.1275 0.6385 1.0002 3.500 0.9341 0.04789 0.03646 -0.1264 0.6296 1.0002 3.750 0.9545 0.05016 0.03869 -0.1259 0.6191 1.0002 4.000 0.9694 0.05268 0.04121 -0.1245 0.6078 1.0002 4.250 0.9818 0.05542 0.04396 -0.1229 0.5961 1.0002 4.500 1.0068 0.05800 0.04652 -0.1228 0.5844 1.0002 4.750 1.0237 0.06143 0.04993 -0.1219 0.5739 1.0002 5.000 1.0327 0.06585 0.05434 -0.1200 0.5619 1.0002