XFOIL Version 6.94 Calculated polar for: gradus32 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.020 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.800 -0.3078 0.04584 0.03476 0.0172 0.9999 0.5294 -2.600 -0.2922 0.04198 0.03072 0.0193 0.9999 0.6117 -2.000 -0.0410 0.03517 0.02325 -0.0198 0.9999 1.0001 -1.800 -0.0256 0.03553 0.02329 -0.0200 0.9999 1.0001 -1.600 -0.0094 0.03594 0.02342 -0.0201 0.9999 1.0001 -1.400 0.0071 0.03641 0.02362 -0.0203 0.9999 1.0001 -1.200 0.0237 0.03691 0.02389 -0.0204 0.9999 1.0001 -1.000 0.0405 0.03744 0.02419 -0.0205 0.9999 1.0001 -0.800 0.0572 0.03800 0.02457 -0.0206 0.9999 1.0001 -0.600 0.0739 0.03860 0.02501 -0.0207 0.9999 1.0001 -0.400 0.0903 0.03924 0.02552 -0.0208 0.9999 1.0001 -0.200 0.1063 0.03992 0.02610 -0.0209 0.9999 1.0001 0.000 0.1219 0.04066 0.02676 -0.0209 0.9999 1.0001 0.200 0.1365 0.04150 0.02757 -0.0210 0.9999 1.0001 0.400 0.1496 0.04250 0.02859 -0.0212 0.9999 1.0001 0.600 0.1591 0.04388 0.03004 -0.0215 0.9999 1.0001 1.000 0.5096 0.04490 0.03118 -0.0771 0.7327 1.0001 1.200 0.5394 0.04580 0.03192 -0.0782 0.7047 1.0001 1.400 0.5656 0.04690 0.03289 -0.0790 0.6835 1.0001 1.600 0.5908 0.04799 0.03384 -0.0795 0.6659 1.0001 1.800 0.6202 0.04874 0.03443 -0.0801 0.6502 1.0001 2.000 0.6249 0.05106 0.03672 -0.0791 0.6371 1.0001 2.200 0.6408 0.05270 0.03826 -0.0788 0.6252 1.0001 2.400 0.6563 0.05437 0.03987 -0.0785 0.6143 1.0001 2.600 0.6645 0.05674 0.04218 -0.0781 0.6065 1.0001 2.800 0.6604 0.06003 0.04546 -0.0773 0.6016 1.0001 3.000 0.6611 0.06305 0.04845 -0.0769 0.5978 1.0001 3.200 0.6638 0.06599 0.05134 -0.0766 0.5950 1.0001 3.400 0.6634 0.06916 0.05447 -0.0762 0.5935 1.0001 3.600 0.6523 0.07297 0.05823 -0.0754 0.5941 1.0001 3.800 0.6277 0.07717 0.06235 -0.0735 0.5975 1.0001 4.000 0.6141 0.08079 0.06590 -0.0725 0.6010 1.0001 4.200 0.6090 0.08407 0.06913 -0.0722 0.6046 1.0001 4.400 0.6114 0.08716 0.07217 -0.0724 0.6083 1.0001 4.600 0.5914 0.09076 0.07572 -0.0714 0.6172 1.0001 4.800 0.5853 0.09398 0.07889 -0.0713 0.6247 1.0001 5.000 0.5930 0.09696 0.08184 -0.0720 0.6292 1.0001