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 = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1712 0.05638 0.04515 -0.0422 0.9998 0.3140 -2.750 -0.1302 0.05481 0.04302 -0.0467 0.9998 0.3036 -2.500 -0.0983 0.05306 0.04109 -0.0485 0.9998 0.2995 -2.250 -0.0653 0.05162 0.03941 -0.0502 0.9998 0.2950 -2.000 -0.0314 0.05046 0.03792 -0.0520 0.9998 0.2904 -1.750 0.0026 0.04956 0.03665 -0.0534 0.9998 0.2868 -1.500 0.0352 0.04885 0.03560 -0.0544 0.9998 0.2850 -1.250 0.0665 0.04824 0.03476 -0.0550 0.9998 0.2851 -1.000 0.0967 0.04771 0.03412 -0.0554 0.9998 0.2881 -0.750 0.1264 0.04730 0.03365 -0.0556 0.9998 0.2939 -0.500 0.1560 0.04704 0.03332 -0.0558 0.9998 0.3017 -0.250 0.1853 0.04670 0.03314 -0.0560 0.9998 0.3116 0.000 0.2146 0.04652 0.03317 -0.0562 0.9998 0.3258 0.250 0.2440 0.04639 0.03349 -0.0568 0.9998 0.3480 0.500 0.2730 0.04646 0.03443 -0.0581 0.9998 0.3950 1.000 0.4473 0.04085 0.02933 -0.0801 0.7854 1.0002 1.250 0.5221 0.03842 0.02625 -0.0857 0.7429 1.0002 1.500 0.6147 0.03604 0.02309 -0.0950 0.7102 1.0002 1.750 0.6868 0.03576 0.02216 -0.1026 0.6803 1.0002 2.000 0.7401 0.03634 0.02225 -0.1073 0.6577 1.0002 2.250 0.7853 0.03725 0.02278 -0.1106 0.6400 1.0002 2.500 0.8221 0.03841 0.02374 -0.1127 0.6258 1.0002 2.750 0.8565 0.03974 0.02497 -0.1146 0.6159 1.0002 3.000 0.8847 0.04127 0.02652 -0.1156 0.6078 1.0002 3.250 0.9206 0.04271 0.02786 -0.1177 0.6000 1.0002 3.500 0.9466 0.04452 0.02971 -0.1184 0.5933 1.0002 3.750 0.9654 0.04662 0.03195 -0.1182 0.5870 1.0002 4.000 0.9878 0.04873 0.03416 -0.1185 0.5814 1.0002 4.250 1.0115 0.05096 0.03647 -0.1191 0.5774 1.0002 4.500 1.0380 0.05324 0.03878 -0.1201 0.5735 1.0002 4.750 1.0350 0.05691 0.04269 -0.1176 0.5713 1.0002 5.000 1.0222 0.06143 0.04742 -0.1143 0.5698 1.0002