XFOIL Version 6.94 Calculated polar for: BL 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 -0.0109 0.04596 0.03673 -0.0739 0.9201 0.2354 -2.750 0.0290 0.04398 0.03434 -0.0761 0.9029 0.2250 -2.500 0.0558 0.04206 0.03234 -0.0757 0.8830 0.2197 -2.250 0.0701 0.04091 0.03112 -0.0729 0.8576 0.2154 -1.750 0.2407 0.03570 0.02282 -0.0915 0.5754 0.2130 -1.500 0.3132 0.03539 0.02146 -0.0997 0.5613 0.2150 -1.250 0.3664 0.03503 0.02077 -0.1042 0.5528 0.2185 -1.000 0.4219 0.03487 0.02029 -0.1092 0.5468 0.2253 -0.750 0.4700 0.03459 0.02003 -0.1130 0.5431 0.2384 -0.500 0.5098 0.03426 0.01989 -0.1153 0.5405 0.2612 -0.250 0.5494 0.03368 0.01990 -0.1178 0.5381 0.3228 0.000 0.5802 0.03184 0.01953 -0.1164 0.5358 1.0002 0.250 0.6193 0.03272 0.01985 -0.1181 0.5330 1.0002 0.500 0.6562 0.03373 0.02057 -0.1200 0.5304 1.0002 0.750 0.6908 0.03469 0.02137 -0.1215 0.5291 1.0002 1.000 0.7227 0.03540 0.02202 -0.1226 0.5294 1.0002 1.250 0.7537 0.03604 0.02266 -0.1234 0.5304 1.0002 1.500 0.7840 0.03678 0.02342 -0.1243 0.5313 1.0002 1.750 0.8140 0.03764 0.02432 -0.1251 0.5319 1.0002 2.000 0.8434 0.03859 0.02532 -0.1259 0.5324 1.0002 2.250 0.8727 0.03951 0.02632 -0.1267 0.5336 1.0002 2.500 0.9019 0.04035 0.02729 -0.1276 0.5368 1.0002 2.750 0.9311 0.04140 0.02845 -0.1286 0.5402 1.0002 3.000 0.9603 0.04272 0.02985 -0.1296 0.5429 1.0002 3.250 0.9876 0.04385 0.03114 -0.1303 0.5458 1.0002 3.500 1.0105 0.04456 0.03220 -0.1306 0.5516 1.0002 3.750 1.0368 0.04607 0.03388 -0.1317 0.5583 1.0002 4.000 1.0553 0.04718 0.03536 -0.1319 0.5667 1.0002 4.250 1.0648 0.04943 0.03799 -0.1314 0.5779 1.0002 4.500 1.0589 0.05326 0.04221 -0.1299 0.5926 1.0002