XFOIL Version 6.94 Calculated polar for: BL BAP 03 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 -0.0682 0.04740 0.03958 -0.0621 0.7753 0.2536 -2.750 -0.0199 0.04439 0.03646 -0.0669 0.7642 0.2463 -2.500 0.0280 0.04234 0.03408 -0.0715 0.7638 0.2393 -2.250 0.0738 0.04087 0.03223 -0.0757 0.7674 0.2356 -2.000 0.1195 0.03969 0.03071 -0.0798 0.7717 0.2341 -1.750 0.1643 0.03879 0.02951 -0.0838 0.7767 0.2334 -1.500 0.2095 0.03819 0.02861 -0.0878 0.7818 0.2332 -1.250 0.2543 0.03776 0.02793 -0.0918 0.7864 0.2348 -1.000 0.2989 0.03748 0.02748 -0.0959 0.7910 0.2386 -0.750 0.3346 0.03811 0.02800 -0.0992 0.7958 0.2447 -0.500 0.3652 0.03958 0.02931 -0.1023 0.8039 0.2535 -0.250 0.3781 0.04239 0.03224 -0.1038 0.8145 0.2623 0.000 0.3889 0.04578 0.03563 -0.1053 0.8275 0.2729 0.250 0.3896 0.04998 0.03984 -0.1055 0.8428 0.2814 0.500 0.3657 0.05493 0.04473 -0.1018 0.8565 0.2810 0.750 0.3523 0.05864 0.04847 -0.0990 0.8677 0.2858 1.000 0.3613 0.06124 0.05120 -0.0992 0.8748 0.3068 1.250 0.3762 0.06300 0.05379 -0.1003 0.8790 0.3948 1.500 0.3518 0.06421 0.05634 -0.0938 0.8891 0.8681 1.750 0.3644 0.06680 0.05841 -0.0936 0.8946 1.0002 2.000 0.3495 0.06962 0.06106 -0.0897 0.9091 1.0002