XFOIL Version 6.94 Calculated polar for: BL BAP 06 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1546 0.05292 0.04253 -0.0426 0.9998 0.2866 -2.750 -0.1162 0.05132 0.04047 -0.0458 0.9998 0.2756 -2.500 -0.0837 0.04962 0.03857 -0.0474 0.9998 0.2708 -2.250 -0.0503 0.04822 0.03694 -0.0491 0.9998 0.2668 -2.000 -0.0170 0.04707 0.03552 -0.0505 0.9998 0.2635 -1.750 0.0158 0.04615 0.03430 -0.0516 0.9998 0.2606 -1.500 0.0486 0.04545 0.03330 -0.0524 0.9998 0.2584 -1.250 0.0800 0.04486 0.03250 -0.0529 0.9998 0.2577 -1.000 0.1107 0.04435 0.03189 -0.0533 0.9998 0.2586 -0.750 0.1407 0.04394 0.03149 -0.0535 0.9998 0.2613 -0.500 0.1700 0.04371 0.03138 -0.0539 0.9998 0.2671 -0.250 0.1967 0.04392 0.03184 -0.0544 0.9998 0.2751 0.000 0.3190 0.03846 0.02709 -0.0727 0.7877 0.3126 0.250 0.4399 0.03042 0.02019 -0.0830 0.7024 1.0002 0.500 0.5474 0.03044 0.01787 -0.0959 0.6461 1.0002 0.750 0.6112 0.03173 0.01800 -0.1026 0.6226 1.0002 1.000 0.6859 0.03415 0.01935 -0.1123 0.6072 1.0002 1.250 0.7321 0.03648 0.02153 -0.1168 0.5941 1.0002 1.500 0.7675 0.03863 0.02368 -0.1191 0.5827 1.0002 1.750 0.7975 0.04056 0.02567 -0.1202 0.5732 1.0002 2.000 0.8256 0.04229 0.02748 -0.1210 0.5664 1.0002 2.250 0.8499 0.04372 0.02907 -0.1211 0.5609 1.0002 2.500 0.8736 0.04533 0.03081 -0.1212 0.5560 1.0002 2.750 0.8971 0.04711 0.03270 -0.1212 0.5510 1.0002 3.000 0.9171 0.04874 0.03449 -0.1208 0.5466 1.0002 3.250 0.9355 0.05044 0.03635 -0.1201 0.5430 1.0002 3.500 0.9551 0.05237 0.03842 -0.1198 0.5406 1.0002 3.750 0.9691 0.05437 0.04063 -0.1188 0.5387 1.0002 4.000 0.9826 0.05662 0.04304 -0.1177 0.5367 1.0002 4.250 0.9884 0.05915 0.04577 -0.1158 0.5348 1.0002 4.500 0.9918 0.06206 0.04885 -0.1138 0.5333 1.0002 4.750 0.9894 0.06554 0.05250 -0.1115 0.5332 1.0002 5.000 0.9775 0.06981 0.05693 -0.1086 0.5347 1.0002