XFOIL Version 6.94 Calculated polar for: Rhode St. Genese 32 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 0.6956 0.01057 0.00430 -0.0875 0.2930 1.0000 1.000 0.7379 0.01078 0.00444 -0.0852 0.2925 1.0000 1.500 0.7815 0.01098 0.00460 -0.0832 0.2919 1.0000 2.000 0.8262 0.01106 0.00459 -0.0814 0.2907 1.0000 2.500 0.8713 0.01134 0.00488 -0.0797 0.2901 1.0000 3.000 0.9165 0.01160 0.00513 -0.0781 0.2893 1.0000 3.500 0.9613 0.01182 0.00536 -0.0764 0.2881 1.0000 4.000 1.0049 0.01189 0.00541 -0.0744 0.2855 1.0000 4.500 1.0474 0.01202 0.00554 -0.0723 0.2817 1.0000 5.000 1.0883 0.01220 0.00574 -0.0698 0.2766 1.0000 5.500 1.1263 0.01242 0.00598 -0.0668 0.2686 1.0000 6.000 1.1521 0.01270 0.00622 -0.0614 0.2519 1.0000 6.500 1.1447 0.01394 0.00683 -0.0505 0.1809 1.0000 7.000 1.1531 0.01517 0.00787 -0.0431 0.1425 1.0000 7.500 1.1511 0.01708 0.00961 -0.0349 0.1034 1.0000 8.000 1.1461 0.01946 0.01161 -0.0274 0.0647 1.0000 8.500 1.1657 0.02101 0.01315 -0.0233 0.0472 1.0000 9.000 1.1701 0.02366 0.01627 -0.0182 0.0306 1.0000 10.000 1.1967 0.02817 0.02084 -0.0120 0.0197 1.0000 10.500 1.2080 0.03088 0.02346 -0.0094 0.0163 1.0000 11.000 1.2053 0.03499 0.02769 -0.0072 0.0141 1.0000 11.500 1.2058 0.03917 0.03209 -0.0052 0.0124 1.0000 12.000 1.1883 0.04600 0.03918 -0.0047 0.0119 1.0000 12.500 1.1852 0.05127 0.04465 -0.0038 0.0118 1.0000 13.000 1.1786 0.05716 0.05077 -0.0035 0.0117 1.0000 13.500 1.1590 0.06543 0.05929 -0.0048 0.0117 1.0000 14.000 1.1473 0.07213 0.06619 -0.0052 0.0117 1.0000