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 = 0.005 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0647 0.07512 0.05313 -0.0187 0.9998 1.0002 -2.750 -0.0696 0.07267 0.05098 -0.0177 0.9998 1.0002 -2.500 -0.0765 0.07011 0.04876 -0.0165 0.9998 1.0002 -2.250 -0.0847 0.06748 0.04644 -0.0154 0.9998 1.0002 -2.000 -0.0863 0.06495 0.04398 -0.0163 0.9998 1.0002 -1.750 -0.0618 0.06310 0.04144 -0.0234 0.9998 1.0002 -1.500 -0.0134 0.06266 0.03930 -0.0332 0.9998 1.0002 -1.250 0.0283 0.06294 0.03787 -0.0379 0.9998 1.0002 -1.000 0.0610 0.06335 0.03698 -0.0397 0.9998 1.0002 -0.750 0.0891 0.06380 0.03644 -0.0403 0.9998 1.0002 -0.500 0.1147 0.06429 0.03615 -0.0405 0.9998 1.0002 -0.250 0.1389 0.06484 0.03606 -0.0405 0.9998 1.0002 0.000 0.1619 0.06546 0.03620 -0.0404 0.9998 1.0002 0.250 0.1839 0.06618 0.03652 -0.0404 0.9998 1.0002 0.500 0.2048 0.06700 0.03706 -0.0403 0.9998 1.0002 0.750 0.2244 0.06797 0.03781 -0.0403 0.9998 1.0002 1.000 0.2425 0.06911 0.03881 -0.0403 0.9998 1.0002 1.250 0.2587 0.07048 0.04012 -0.0404 0.9998 1.0002 1.500 0.2722 0.07216 0.04177 -0.0406 0.9998 1.0002 1.750 0.2826 0.07420 0.04379 -0.0409 0.9998 1.0002 2.000 0.2900 0.07661 0.04616 -0.0412 0.9998 1.0002 2.250 0.2952 0.07931 0.04878 -0.0417 0.9998 1.0002 2.500 0.2998 0.08216 0.05151 -0.0423 0.9998 1.0002 2.750 0.3048 0.08504 0.05426 -0.0431 0.9998 1.0002 3.000 0.3108 0.08790 0.05696 -0.0440 0.9998 1.0002 3.250 0.3177 0.09073 0.05962 -0.0449 0.9998 1.0002 3.500 0.3255 0.09350 0.06222 -0.0459 0.9998 1.0002 3.750 0.3339 0.09623 0.06478 -0.0468 0.9998 1.0002 4.000 0.3429 0.09892 0.06731 -0.0478 0.9998 1.0002 4.250 0.3524 0.10159 0.06983 -0.0488 0.9998 1.0002 4.500 0.3624 0.10423 0.07232 -0.0497 0.9998 1.0002 4.750 0.3726 0.10687 0.07482 -0.0507 0.9998 1.0002 5.000 0.3831 0.10949 0.07731 -0.0517 0.9998 1.0002