XFOIL Version 6.94 Calculated polar for: GD BAP 02 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 -0.0655 0.07781 0.05500 -0.0212 0.9998 1.0002 -2.750 -0.0709 0.07542 0.05292 -0.0200 0.9998 1.0002 -2.500 -0.0782 0.07293 0.05076 -0.0187 0.9998 1.0002 -2.250 -0.0870 0.07035 0.04852 -0.0172 0.9998 1.0002 -2.000 -0.0933 0.06779 0.04614 -0.0168 0.9998 1.0002 -1.750 -0.0806 0.06562 0.04365 -0.0213 0.9998 1.0002 -1.500 -0.0369 0.06469 0.04134 -0.0315 0.9998 1.0002 -1.250 0.0102 0.06488 0.03967 -0.0387 0.9998 1.0002 -1.000 0.0464 0.06532 0.03862 -0.0414 0.9998 1.0002 -0.750 0.0761 0.06580 0.03795 -0.0423 0.9998 1.0002 -0.500 0.1027 0.06630 0.03755 -0.0426 0.9998 1.0002 -0.250 0.1275 0.06684 0.03736 -0.0426 0.9998 1.0002 0.000 0.1512 0.06742 0.03734 -0.0424 0.9998 1.0002 0.250 0.1741 0.06806 0.03751 -0.0423 0.9998 1.0002 0.500 0.1962 0.06876 0.03784 -0.0421 0.9998 1.0002 0.750 0.2176 0.06955 0.03834 -0.0419 0.9998 1.0002 1.000 0.2382 0.07043 0.03900 -0.0418 0.9998 1.0002 1.250 0.2578 0.07144 0.03986 -0.0417 0.9998 1.0002 1.500 0.2763 0.07259 0.04095 -0.0417 0.9998 1.0002 1.750 0.2932 0.07395 0.04229 -0.0417 0.9998 1.0002 2.000 0.3080 0.07556 0.04395 -0.0419 0.9998 1.0002 2.250 0.3199 0.07752 0.04599 -0.0421 0.9998 1.0002 2.500 0.3283 0.07992 0.04846 -0.0425 0.9998 1.0002 2.750 0.3332 0.08275 0.05133 -0.0430 0.9998 1.0002 3.000 0.3362 0.08587 0.05442 -0.0437 0.9998 1.0002 3.250 0.3393 0.08906 0.05753 -0.0446 0.9998 1.0002 3.500 0.3437 0.09221 0.06056 -0.0455 0.9998 1.0002 3.750 0.3494 0.09525 0.06348 -0.0465 0.9998 1.0002 4.000 0.3561 0.09822 0.06631 -0.0475 0.9998 1.0002 4.250 0.3638 0.10110 0.06907 -0.0485 0.9998 1.0002 4.500 0.3721 0.10394 0.07177 -0.0495 0.9998 1.0002 4.750 0.3811 0.10673 0.07444 -0.0505 0.9998 1.0002 5.000 0.3905 0.10949 0.07708 -0.0515 0.9998 1.0002