XFOIL Version 6.94 Calculated polar for: dae41 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.3636 0.00681 0.00241 -0.0576 0.6807 0.9450 1.000 0.4438 0.00684 0.00230 -0.0623 0.6624 0.9827 1.500 0.5268 0.00693 0.00225 -0.0679 0.6413 1.0000 2.000 0.5741 0.00708 0.00231 -0.0662 0.6202 1.0000 2.500 0.6233 0.00726 0.00237 -0.0648 0.5977 1.0000 3.000 0.6735 0.00750 0.00248 -0.0636 0.5740 1.0000 3.500 0.7250 0.00773 0.00265 -0.0626 0.5484 1.0000 4.000 0.7764 0.00806 0.00286 -0.0617 0.5213 1.0000 4.500 0.8281 0.00839 0.00312 -0.0608 0.4920 1.0000 5.000 0.8791 0.00880 0.00345 -0.0599 0.4608 1.0000 5.500 0.9291 0.00928 0.00382 -0.0589 0.4203 1.0000 6.000 0.9767 0.00995 0.00428 -0.0576 0.3758 1.0000 6.500 1.0240 0.01065 0.00485 -0.0563 0.3299 1.0000 7.000 1.0687 0.01152 0.00551 -0.0547 0.2816 1.0000 7.500 1.1109 0.01253 0.00631 -0.0528 0.2342 1.0000 8.000 1.1518 0.01357 0.00718 -0.0507 0.1914 1.0000 8.500 1.1895 0.01474 0.00818 -0.0482 0.1540 1.0000 9.000 1.2237 0.01599 0.00929 -0.0452 0.1212 1.0000 9.500 1.2515 0.01732 0.01052 -0.0413 0.0944 1.0000 10.000 1.2716 0.01887 0.01200 -0.0364 0.0749 1.0000 10.500 1.2909 0.02065 0.01378 -0.0320 0.0623 1.0000 11.000 1.3055 0.02294 0.01608 -0.0278 0.0529 1.0000 11.500 1.3278 0.02491 0.01818 -0.0249 0.0473 1.0000 12.000 1.3382 0.02792 0.02128 -0.0216 0.0424 1.0000 12.500 1.3547 0.03069 0.02420 -0.0192 0.0389 1.0000 13.000 1.3568 0.03488 0.02847 -0.0167 0.0359 1.0000 13.500 1.3668 0.03867 0.03247 -0.0150 0.0339 1.0000 14.000 1.3750 0.04288 0.03684 -0.0139 0.0319 1.0000 14.500 1.3788 0.04781 0.04191 -0.0134 0.0303 1.0000 15.000 1.3702 0.05438 0.04863 -0.0131 0.0286 1.0000 15.500 1.3772 0.05970 0.05418 -0.0137 0.0277 1.0000 16.000 1.3787 0.06594 0.06065 -0.0148 0.0266 1.0000 16.500 1.3787 0.07268 0.06759 -0.0164 0.0257 1.0000 17.000 1.3765 0.08002 0.07511 -0.0186 0.0248 1.0000 17.500 1.3730 0.08778 0.08305 -0.0213 0.0242 1.0000 18.000 1.3664 0.09605 0.09150 -0.0242 0.0235 1.0000 18.500 1.3532 0.10583 0.10156 -0.0280 0.0230 1.0000 19.000 1.3388 0.11658 0.11262 -0.0335 0.0227 1.0000 19.500 1.3198 0.12866 0.12501 -0.0402 0.0225 1.0000 20.000 1.2951 0.14245 0.13913 -0.0486 0.0223 1.0000 20.500 1.2596 0.15938 0.15640 -0.0596 0.0223 1.0000 21.500 0.8089 0.24616 0.24432 -0.1085 0.0294 1.0000 22.000 0.8198 0.25496 0.25316 -0.1112 0.0285 1.0000 22.500 0.8158 0.26681 0.26502 -0.1178 0.0251 1.0000 23.000 0.8281 0.27257 0.27081 -0.1204 0.0237 1.0000 23.500 0.8381 0.28146 0.27973 -0.1232 0.0229 1.0000 24.000 0.8392 0.29211 0.29041 -0.1285 0.0193 1.0000 24.500 0.8537 0.29754 0.29588 -0.1302 0.0185 1.0000 25.000 0.8517 0.31170 0.31004 -0.1361 0.0157 1.0000 25.500 0.8614 0.31829 0.31666 -0.1388 0.0148 1.0000 26.000 0.8646 0.33133 0.32971 -0.1432 0.0138 1.0000 26.500 0.8713 0.34072 0.33912 -0.1467 0.0122 1.0000 27.000 0.8792 0.34786 0.34630 -0.1496 0.0115 1.0000 27.500 0.8851 0.35809 0.35654 -0.1530 0.0111 1.0000 28.000 0.8889 0.37046 0.36892 -0.1571 0.0098 1.0000 28.500 0.8950 0.37900 0.37749 -0.1603 0.0089 1.0000 29.000 0.9023 0.38681 0.38533 -0.1628 0.0085 1.0000 29.500 0.9061 0.39719 0.39572 -0.1665 0.0085 1.0000