XFOIL Version 6.94 Calculated polar for: BL BAP 05 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 -0.0054 0.04500 0.03557 -0.0729 0.8957 0.2295 -2.750 0.0100 0.04316 0.03378 -0.0706 0.8743 0.2255 -2.500 0.0068 0.04231 0.03308 -0.0648 0.8385 0.2228 -2.250 0.2096 0.03706 0.02426 -0.0962 0.6072 0.2128 -2.000 0.2824 0.03662 0.02311 -0.1051 0.5947 0.2141 -1.750 0.3478 0.03668 0.02271 -0.1123 0.5845 0.2158 -1.500 0.3940 0.03654 0.02244 -0.1157 0.5799 0.2191 -1.250 0.4321 0.03625 0.02212 -0.1173 0.5777 0.2243 -1.000 0.4685 0.03593 0.02188 -0.1187 0.5765 0.2329 -0.750 0.5037 0.03566 0.02178 -0.1200 0.5763 0.2502 -0.500 0.5383 0.03534 0.02177 -0.1214 0.5763 0.2805 -0.250 0.5636 0.03268 0.02156 -0.1199 0.5763 1.0002 0.000 0.5997 0.03337 0.02154 -0.1205 0.5763 1.0002 0.250 0.6334 0.03405 0.02188 -0.1215 0.5770 1.0002 0.500 0.6670 0.03476 0.02238 -0.1229 0.5795 1.0002 0.750 0.7007 0.03543 0.02291 -0.1244 0.5830 1.0002 1.000 0.7308 0.03486 0.02241 -0.1250 0.5882 1.0002 1.250 0.7623 0.03499 0.02258 -0.1262 0.5935 1.0002 1.500 0.7949 0.03550 0.02311 -0.1277 0.5982 1.0002 1.750 0.8284 0.03626 0.02387 -0.1295 0.6025 1.0002 2.000 0.8571 0.03613 0.02400 -0.1306 0.6108 1.0002 2.250 0.8854 0.03654 0.02470 -0.1322 0.6211 1.0002 2.500 0.9082 0.03758 0.02614 -0.1334 0.6341 1.0002 2.750 0.9242 0.03950 0.02845 -0.1344 0.6486 1.0002 3.000 0.9308 0.04261 0.03186 -0.1345 0.6642 1.0002 3.250 0.8569 0.05076 0.04040 -0.1250 0.6797 1.0002 3.500 0.7441 0.06351 0.05324 -0.1138 0.6940 1.0002 4.000 0.7442 0.07206 0.06171 -0.1124 0.6901 1.0002 4.250 0.7144 0.07746 0.06708 -0.1087 0.6862 1.0002 4.500 0.7124 0.08081 0.07040 -0.1069 0.6764 1.0002 4.750 0.7396 0.08280 0.07234 -0.1074 0.6634 1.0002 5.000 0.7464 0.08558 0.07509 -0.1062 0.6505 1.0002