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 = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1843 0.05830 0.04640 -0.0384 0.9998 0.3485 -2.750 -0.1448 0.05625 0.04394 -0.0430 0.9998 0.3384 -2.500 -0.1049 0.05485 0.04196 -0.0470 0.9998 0.3303 -2.250 -0.0712 0.05337 0.04023 -0.0489 0.9998 0.3265 -2.000 -0.0372 0.05218 0.03874 -0.0507 0.9998 0.3236 -1.750 -0.0036 0.05121 0.03747 -0.0522 0.9998 0.3231 -1.500 0.0291 0.05044 0.03640 -0.0534 0.9998 0.3252 -1.250 0.0612 0.04983 0.03553 -0.0543 0.9998 0.3292 -1.000 0.0921 0.04921 0.03480 -0.0549 0.9998 0.3347 -0.750 0.1220 0.04865 0.03427 -0.0552 0.9998 0.3428 -0.500 0.1522 0.04829 0.03388 -0.0555 0.9998 0.3534 -0.250 0.1818 0.04785 0.03369 -0.0558 0.9998 0.3704 0.000 0.2117 0.04745 0.03369 -0.0562 0.9998 0.3993 0.250 0.2429 0.04678 0.03397 -0.0569 0.9998 0.4636 0.500 0.2450 0.04462 0.03364 -0.0518 0.9998 1.0002 0.750 0.2697 0.04617 0.03470 -0.0521 0.9998 1.0002 1.000 0.3890 0.04970 0.03736 -0.0768 0.8955 1.0002 1.250 0.4440 0.04895 0.03607 -0.0826 0.8226 1.0002 1.500 0.4954 0.04847 0.03517 -0.0866 0.7807 1.0002 1.750 0.5629 0.04702 0.03333 -0.0920 0.7544 1.0002 2.000 0.6269 0.04580 0.03179 -0.0971 0.7346 1.0002 2.500 0.7259 0.04649 0.03199 -0.1049 0.6994 1.0002 2.750 0.7732 0.04706 0.03232 -0.1084 0.6847 1.0002 3.000 0.8114 0.04823 0.03333 -0.1107 0.6717 1.0002 3.250 0.8325 0.05058 0.03565 -0.1113 0.6627 1.0002 3.500 0.8313 0.05448 0.03962 -0.1096 0.6564 1.0002 3.750 0.8423 0.05777 0.04290 -0.1095 0.6506 1.0002 4.000 0.8807 0.05932 0.04436 -0.1119 0.6439 1.0002 4.250 0.8451 0.06591 0.05105 -0.1075 0.6420 1.0002 4.500 0.8116 0.07275 0.05792 -0.1040 0.6416 1.0002 4.750 0.7929 0.07895 0.06413 -0.1028 0.6422 1.0002 5.000 0.7884 0.08416 0.06933 -0.1028 0.6441 1.0002