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 = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1003 0.05100 0.04199 -0.0567 0.9769 0.2635 -2.750 -0.0337 0.04837 0.03877 -0.0651 0.9631 0.2475 -2.500 0.0255 0.04567 0.03573 -0.0716 0.9470 0.2392 -2.000 0.1127 0.04153 0.03102 -0.0770 0.9022 0.2337 -1.750 0.1228 0.04036 0.02982 -0.0730 0.8571 0.2330 -1.500 0.1547 0.03851 0.02771 -0.0725 0.7116 0.2326 -1.250 0.2795 0.03476 0.02228 -0.0878 0.6142 0.2361 -1.000 0.3334 0.03425 0.02097 -0.0920 0.5928 0.2424 -0.750 0.3864 0.03406 0.02007 -0.0962 0.5811 0.2551 -0.500 0.4364 0.03364 0.01948 -0.1003 0.5746 0.2779 -0.250 0.4852 0.03296 0.01910 -0.1044 0.5699 0.3260 0.000 0.5229 0.03064 0.01835 -0.1045 0.5668 1.0002 0.250 0.5732 0.03144 0.01825 -0.1081 0.5636 1.0002 0.500 0.6200 0.03233 0.01867 -0.1119 0.5605 1.0002 0.750 0.6592 0.03307 0.01924 -0.1144 0.5578 1.0002 1.000 0.6977 0.03390 0.01995 -0.1169 0.5553 1.0002 1.250 0.7344 0.03470 0.02070 -0.1190 0.5544 1.0002 1.500 0.7694 0.03548 0.02148 -0.1209 0.5548 1.0002 1.750 0.8033 0.03631 0.02234 -0.1225 0.5554 1.0002 2.000 0.8360 0.03725 0.02333 -0.1240 0.5557 1.0002 2.250 0.8674 0.03830 0.02445 -0.1253 0.5558 1.0002 2.500 0.8975 0.03943 0.02570 -0.1265 0.5561 1.0002 2.750 0.9273 0.04061 0.02699 -0.1276 0.5578 1.0002 3.000 0.9575 0.04194 0.02842 -0.1290 0.5603 1.0002 3.250 0.9847 0.04311 0.02977 -0.1298 0.5627 1.0002 3.500 1.0058 0.04427 0.03126 -0.1299 0.5663 1.0002 3.750 1.0237 0.04592 0.03324 -0.1299 0.5711 1.0002 4.000 1.0412 0.04799 0.03557 -0.1301 0.5777 1.0002 4.250 1.0541 0.05054 0.03838 -0.1300 0.5846 1.0002 4.500 1.0119 0.05662 0.04497 -0.1245 0.6018 1.0002