XFOIL Version 6.94 Calculated polar for: GD BAP 01 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1603 0.05239 0.04207 -0.0357 0.9998 0.3074 -2.750 -0.1277 0.04982 0.03947 -0.0377 0.9998 0.3020 -2.500 -0.0923 0.04786 0.03737 -0.0401 0.9998 0.2959 -2.250 -0.0552 0.04628 0.03558 -0.0426 0.9998 0.2904 -2.000 -0.0171 0.04503 0.03409 -0.0451 0.9998 0.2864 -1.750 0.0204 0.04408 0.03305 -0.0477 0.9998 0.2842 -1.500 0.1289 0.04127 0.03007 -0.0649 0.9385 0.2865 -1.250 0.1436 0.04008 0.02902 -0.0638 0.8190 0.2886 -1.000 0.2553 0.03622 0.02448 -0.0766 0.7464 0.3102 -0.750 0.3807 0.03294 0.02060 -0.0932 0.7074 0.3725 -0.500 0.4294 0.03015 0.01943 -0.0953 0.6911 1.0002 -0.250 0.4842 0.03136 0.01911 -0.0991 0.6771 1.0002 0.000 0.5270 0.03250 0.01952 -0.1019 0.6670 1.0002 0.250 0.5670 0.03357 0.02018 -0.1047 0.6616 1.0002 0.500 0.6042 0.03455 0.02095 -0.1073 0.6597 1.0002 0.750 0.6390 0.03555 0.02186 -0.1096 0.6594 1.0002 1.000 0.6716 0.03664 0.02291 -0.1116 0.6597 1.0002 1.250 0.7020 0.03784 0.02414 -0.1134 0.6602 1.0002 1.500 0.7303 0.03923 0.02557 -0.1149 0.6602 1.0002 1.750 0.7575 0.04086 0.02723 -0.1162 0.6588 1.0002 2.000 0.7862 0.04273 0.02909 -0.1178 0.6559 1.0002 2.250 0.8075 0.04480 0.03126 -0.1184 0.6537 1.0002 2.500 0.8250 0.04708 0.03365 -0.1188 0.6534 1.0002 2.750 0.8387 0.04967 0.03636 -0.1189 0.6546 1.0002 3.000 0.8377 0.05307 0.03992 -0.1176 0.6570 1.0002 3.250 0.8148 0.05787 0.04488 -0.1143 0.6610 1.0002 3.500 0.7947 0.06290 0.04996 -0.1115 0.6636 1.0002 4.000 0.7176 0.07519 0.06227 -0.1032 0.6688 1.0002 4.250 0.7266 0.07867 0.06570 -0.1032 0.6640 1.0002 4.500 0.7149 0.08302 0.07002 -0.1014 0.6606 1.0002 4.750 0.7266 0.08641 0.07337 -0.1017 0.6561 1.0002 5.000 0.7212 0.09042 0.07735 -0.1007 0.6531 1.0002