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 = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1608 0.05432 0.04332 -0.0411 0.9998 0.3094 -2.750 -0.1238 0.05268 0.04129 -0.0442 0.9998 0.3024 -2.500 -0.0907 0.05095 0.03936 -0.0461 0.9998 0.2981 -2.250 -0.0568 0.04951 0.03766 -0.0479 0.9998 0.2934 -2.000 -0.0219 0.04836 0.03616 -0.0496 0.9998 0.2890 -1.750 0.0123 0.04746 0.03489 -0.0510 0.9998 0.2861 -1.500 0.0452 0.04671 0.03386 -0.0520 0.9998 0.2851 -1.250 0.0767 0.04606 0.03305 -0.0526 0.9998 0.2865 -1.000 0.1072 0.04551 0.03245 -0.0530 0.9998 0.2910 -0.750 0.1373 0.04512 0.03202 -0.0533 0.9998 0.2980 -0.500 0.1671 0.04489 0.03182 -0.0537 0.9998 0.3063 -0.250 0.1954 0.04465 0.03195 -0.0542 0.9998 0.3179 0.000 0.2159 0.04566 0.03342 -0.0551 0.9998 0.3299 0.250 0.3362 0.03805 0.02896 -0.0735 0.8195 0.9864 0.500 0.4209 0.03574 0.02492 -0.0792 0.7544 1.0002 0.750 0.5374 0.03302 0.02055 -0.0917 0.7049 1.0002 1.000 0.6134 0.03323 0.01973 -0.1002 0.6726 1.0002 1.250 0.6631 0.03422 0.02017 -0.1046 0.6532 1.0002 1.500 0.7090 0.03539 0.02089 -0.1083 0.6380 1.0002 1.750 0.7548 0.03674 0.02181 -0.1120 0.6252 1.0002 2.000 0.8043 0.03853 0.02314 -0.1164 0.6147 1.0002 2.250 0.8467 0.04064 0.02507 -0.1200 0.6072 1.0002 2.500 0.8787 0.04261 0.02713 -0.1218 0.6016 1.0002 2.750 0.9066 0.04465 0.02930 -0.1229 0.5967 1.0002 3.000 0.9339 0.04695 0.03169 -0.1240 0.5914 1.0002 3.250 0.9535 0.04921 0.03414 -0.1239 0.5863 1.0002 3.500 0.9712 0.05166 0.03678 -0.1235 0.5817 1.0002 3.750 0.9856 0.05416 0.03952 -0.1228 0.5785 1.0002 4.000 1.0001 0.05686 0.04239 -0.1223 0.5765 1.0002 4.250 1.0146 0.05987 0.04553 -0.1219 0.5743 1.0002 4.500 1.0141 0.06321 0.04910 -0.1198 0.5733 1.0002 4.750 1.0082 0.06707 0.05315 -0.1173 0.5732 1.0002 5.000 0.9765 0.07218 0.05849 -0.1129 0.5781 1.0002