XFOIL Version 6.94 Calculated polar for: AH 94-156 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.3373 0.01212 0.00748 -0.0608 0.7110 0.8915 0.500 0.3905 0.01214 0.00744 -0.0597 0.7052 0.9028 1.000 0.4452 0.01197 0.00717 -0.0593 0.7001 0.9121 1.500 0.4984 0.01194 0.00713 -0.0590 0.6937 0.9196 2.000 0.5444 0.01177 0.00694 -0.0575 0.6867 0.9271 2.500 0.6043 0.01150 0.00661 -0.0586 0.6811 0.9307 3.000 0.6551 0.01138 0.00653 -0.0581 0.6729 0.9352 3.500 0.7060 0.01116 0.00630 -0.0577 0.6649 0.9391 4.000 0.7526 0.01104 0.00620 -0.0564 0.6562 0.9426 4.500 0.8020 0.01076 0.00593 -0.0557 0.6457 0.9453 5.000 0.8506 0.01060 0.00585 -0.0549 0.6339 0.9474 5.500 0.9004 0.01044 0.00570 -0.0542 0.6206 0.9499 6.000 0.9472 0.01037 0.00564 -0.0531 0.6048 0.9516 6.500 0.9881 0.01038 0.00572 -0.0509 0.5853 0.9545 7.000 1.0250 0.01049 0.00589 -0.0481 0.5622 0.9566 7.500 1.0536 0.01071 0.00611 -0.0437 0.5364 0.9592 8.000 1.0740 0.01127 0.00660 -0.0382 0.5035 0.9625 8.500 1.0930 0.01226 0.00752 -0.0333 0.4658 0.9666 9.000 1.1144 0.01365 0.00883 -0.0297 0.4281 0.9711 10.000 1.1647 0.01781 0.01277 -0.0268 0.3401 0.9993 10.500 1.1724 0.02026 0.01508 -0.0225 0.2937 1.0000 11.000 1.1745 0.02332 0.01789 -0.0182 0.2412 1.0000 11.500 1.1803 0.02645 0.02081 -0.0147 0.1920 1.0000 12.000 1.1832 0.03006 0.02416 -0.0114 0.1395 1.0000 12.500 1.1841 0.03409 0.02792 -0.0085 0.0904 1.0000 13.000 1.1856 0.03837 0.03200 -0.0061 0.0550 1.0000 13.500 1.1888 0.04284 0.03639 -0.0042 0.0330 1.0000 14.000 1.1927 0.04753 0.04118 -0.0028 0.0230 1.0000 14.500 1.1870 0.05353 0.04730 -0.0015 0.0175 1.0000 15.000 1.1963 0.05828 0.05225 -0.0013 0.0158 1.0000 15.500 1.2001 0.06382 0.05796 -0.0014 0.0141 1.0000 16.000 1.2017 0.06988 0.06421 -0.0019 0.0132 1.0000 16.500 1.1953 0.07718 0.07168 -0.0028 0.0120 1.0000 17.000 1.1791 0.08574 0.08053 -0.0036 0.0110 1.0000 17.500 1.1839 0.09205 0.08705 -0.0052 0.0107 1.0000 18.000 1.1879 0.09876 0.09398 -0.0073 0.0101 1.0000 18.500 1.1880 0.10600 0.10149 -0.0095 0.0097 1.0000 19.000 1.1854 0.11392 0.10967 -0.0124 0.0093 1.0000 19.500 1.1800 0.12256 0.11858 -0.0160 0.0090 1.0000 20.000 1.1712 0.13197 0.12826 -0.0206 0.0088 1.0000 20.500 1.1592 0.14236 0.13892 -0.0261 0.0085 1.0000 21.000 1.1434 0.15385 0.15069 -0.0327 0.0084 1.0000 21.500 1.1225 0.16693 0.16406 -0.0405 0.0083 1.0000 22.000 1.0921 0.18291 0.18035 -0.0503 0.0083 1.0000