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 = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1584 0.05274 0.04380 -0.0453 0.9998 0.2754 -2.750 -0.1190 0.05031 0.04095 -0.0488 0.9998 0.2463 -2.500 -0.0802 0.04876 0.03883 -0.0514 0.9998 0.2254 -2.250 -0.0481 0.04709 0.03699 -0.0528 0.9998 0.2156 -2.000 -0.0133 0.04652 0.03587 -0.0539 0.9998 0.2046 -1.750 0.0165 0.04525 0.03458 -0.0546 0.9998 0.2007 -1.500 0.0465 0.04437 0.03357 -0.0551 0.9998 0.1966 -1.250 0.0769 0.04371 0.03278 -0.0555 0.9998 0.1932 -1.000 0.1067 0.04323 0.03222 -0.0558 0.9998 0.1923 -0.750 0.1359 0.04285 0.03185 -0.0560 0.9998 0.1933 -0.500 0.1649 0.04260 0.03164 -0.0561 0.9998 0.1951 -0.250 0.3425 0.03721 0.02604 -0.0817 0.9071 0.2046 0.000 0.3216 0.03569 0.02482 -0.0712 0.7659 0.2052 0.250 0.5018 0.02943 0.01707 -0.0952 0.5698 0.2669 0.500 0.5306 0.02706 0.01627 -0.0938 0.5439 1.0002 0.750 0.5736 0.02770 0.01587 -0.0958 0.5243 1.0002 1.000 0.6154 0.02827 0.01588 -0.0983 0.5091 1.0002 1.250 0.6589 0.02886 0.01606 -0.1014 0.4981 1.0002 1.500 0.7024 0.02946 0.01638 -0.1047 0.4894 1.0002 1.750 0.7498 0.03018 0.01677 -0.1088 0.4824 1.0002 2.000 0.7894 0.03081 0.01735 -0.1113 0.4764 1.0002 2.250 0.8290 0.03154 0.01799 -0.1139 0.4703 1.0002 2.500 0.8686 0.03241 0.01871 -0.1164 0.4647 1.0002 2.750 0.9054 0.03337 0.01958 -0.1184 0.4603 1.0002 3.000 0.9378 0.03430 0.02059 -0.1196 0.4571 1.0002 3.250 0.9685 0.03535 0.02170 -0.1205 0.4538 1.0002 3.500 0.9984 0.03646 0.02289 -0.1212 0.4502 1.0002 3.750 1.0280 0.03767 0.02412 -0.1219 0.4466 1.0002 4.000 1.0578 0.03901 0.02546 -0.1226 0.4433 1.0002 4.250 1.0874 0.04055 0.02703 -0.1234 0.4409 1.0002 4.500 1.1123 0.04202 0.02870 -0.1234 0.4389 1.0002 4.750 1.1347 0.04354 0.03047 -0.1229 0.4366 1.0002 5.000 1.1559 0.04521 0.03237 -0.1223 0.4341 1.0002