XFOIL Version 6.94 Calculated polar for: woubair3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.012 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0831 0.04755 0.02993 -0.0055 0.9988 1.0012 -2.750 -0.0575 0.04775 0.02999 -0.0056 0.9988 1.0012 -2.500 -0.0317 0.04798 0.03009 -0.0056 0.9988 1.0012 -2.250 -0.0058 0.04824 0.03024 -0.0058 0.9988 1.0012 -2.000 0.0204 0.04853 0.03041 -0.0060 0.9988 1.0012 -1.750 0.0468 0.04884 0.03062 -0.0062 0.9988 1.0012 -1.500 0.0733 0.04918 0.03086 -0.0064 0.9988 1.0012 -1.250 0.0999 0.04953 0.03114 -0.0067 0.9988 1.0012 -1.000 0.1267 0.04989 0.03143 -0.0070 0.9988 1.0012 -0.750 0.1537 0.05027 0.03178 -0.0073 0.9988 1.0012 -0.500 0.1810 0.05066 0.03220 -0.0075 0.9988 1.0012 -0.250 0.2086 0.05105 0.03270 -0.0079 0.9988 1.0012 0.000 0.2368 0.05143 0.03331 -0.0083 0.9988 1.0012 0.250 0.2665 0.05179 0.03407 -0.0089 0.9988 1.0012 0.500 0.2984 0.05215 0.03506 -0.0102 0.9988 1.0012 0.750 0.3309 0.05289 0.03671 -0.0127 0.9988 1.0012 1.000 0.3466 0.05584 0.04054 -0.0160 0.9988 1.0012 1.250 0.4396 0.06099 0.04599 -0.0422 0.8721 1.0012 1.500 0.4973 0.06190 0.04683 -0.0503 0.7878 1.0012 2.000 0.7254 0.05914 0.04370 -0.0737 0.6630 1.0012 2.250 0.7584 0.06256 0.04705 -0.0767 0.6460 1.0012 2.500 0.7857 0.06626 0.05071 -0.0786 0.6296 1.0012 2.750 0.8166 0.07005 0.05443 -0.0807 0.6143 1.0012 3.000 0.8134 0.07522 0.05977 -0.0807 0.6129 1.0012 3.250 0.8082 0.08072 0.06535 -0.0808 0.6137 1.0012 3.750 0.7411 0.09381 0.07838 -0.0771 0.6307 1.0012 4.000 0.7374 0.09940 0.08390 -0.0778 0.6343 1.0012 4.250 0.7049 0.10543 0.08983 -0.0765 0.6467 1.0012 4.500 0.7029 0.11064 0.09497 -0.0775 0.6526 1.0012 5.000 0.6858 0.12077 0.10498 -0.0788 0.6738 1.0012