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 = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1579 0.05313 0.04369 -0.0454 0.9998 0.2729 -2.750 -0.1173 0.05114 0.04117 -0.0492 0.9998 0.2492 -2.500 -0.0824 0.04922 0.03893 -0.0514 0.9998 0.2356 -2.250 -0.0480 0.04822 0.03751 -0.0529 0.9998 0.2254 -2.000 -0.0172 0.04689 0.03607 -0.0538 0.9998 0.2196 -1.750 0.0144 0.04590 0.03483 -0.0546 0.9998 0.2137 -1.500 0.0459 0.04523 0.03388 -0.0553 0.9998 0.2101 -1.250 0.0757 0.04466 0.03317 -0.0557 0.9998 0.2094 -1.000 0.1047 0.04415 0.03261 -0.0559 0.9998 0.2101 -0.750 0.1337 0.04377 0.03220 -0.0559 0.9998 0.2112 -0.500 0.1632 0.04352 0.03195 -0.0560 0.9998 0.2125 -0.250 0.1926 0.04339 0.03191 -0.0562 0.9998 0.2142 0.000 0.3610 0.03816 0.02681 -0.0806 0.9066 0.2328 0.250 0.3709 0.03521 0.02415 -0.0750 0.7427 0.2433 0.500 0.5120 0.02756 0.01716 -0.0906 0.6102 1.0002 0.750 0.5667 0.02823 0.01643 -0.0947 0.5723 1.0002 1.000 0.6101 0.02894 0.01642 -0.0975 0.5505 1.0002 1.250 0.6505 0.02959 0.01665 -0.1000 0.5343 1.0002 1.500 0.6942 0.03033 0.01699 -0.1033 0.5224 1.0002 1.750 0.7358 0.03103 0.01750 -0.1062 0.5132 1.0002 2.000 0.7809 0.03185 0.01804 -0.1098 0.5058 1.0002 2.250 0.8206 0.03265 0.01877 -0.1125 0.4995 1.0002 2.500 0.8582 0.03349 0.01958 -0.1147 0.4930 1.0002 2.750 0.8961 0.03444 0.02045 -0.1169 0.4869 1.0002 3.000 0.9338 0.03555 0.02144 -0.1192 0.4821 1.0002 3.250 0.9649 0.03660 0.02262 -0.1202 0.4788 1.0002 3.500 0.9949 0.03776 0.02391 -0.1211 0.4752 1.0002 3.750 1.0238 0.03902 0.02526 -0.1217 0.4714 1.0002 4.000 1.0525 0.04037 0.02666 -0.1223 0.4675 1.0002 4.250 1.0814 0.04186 0.02817 -0.1230 0.4642 1.0002 4.500 1.1095 0.04354 0.02993 -0.1236 0.4619 1.0002 4.750 1.1312 0.04522 0.03187 -0.1232 0.4598 1.0002 5.000 1.1505 0.04707 0.03396 -0.1224 0.4574 1.0002