XFOIL Version 6.96 Calculated polar for: S9033 (7.5%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.750 -0.6111 0.09132 0.08422 0.0347 1.0000 0.3624 -7.500 -0.7269 0.06369 0.05645 -0.0066 1.0000 0.1544 -7.250 -0.7194 0.05794 0.05051 -0.0079 1.0000 0.1506 -7.000 -0.7153 0.05124 0.04332 -0.0100 1.0000 0.1467 -6.750 -0.7047 0.04581 0.03735 -0.0107 1.0000 0.1466 -6.500 -0.6894 0.04193 0.03293 -0.0107 1.0000 0.1533 -6.250 -0.6702 0.03889 0.02967 -0.0101 1.0000 0.1619 -6.000 -0.6507 0.03515 0.02516 -0.0097 1.0000 0.1691 -5.750 -0.6289 0.03282 0.02254 -0.0089 1.0000 0.1838 -5.500 -0.6057 0.03058 0.02018 -0.0081 1.0000 0.1992 -5.250 -0.5821 0.02878 0.01834 -0.0072 1.0000 0.2180 -5.000 -0.5580 0.02693 0.01619 -0.0064 1.0000 0.2404 -4.750 -0.5337 0.02530 0.01465 -0.0054 1.0000 0.2647 -4.500 -0.5098 0.02389 0.01321 -0.0044 1.0000 0.2974 -4.250 -0.4858 0.02254 0.01207 -0.0032 1.0000 0.3330 -4.000 -0.4625 0.02136 0.01101 -0.0019 1.0000 0.3787 -3.750 -0.4398 0.02026 0.01018 -0.0003 1.0000 0.4324 -3.500 -0.4182 0.01927 0.00946 0.0017 1.0000 0.4965 -3.250 -0.3979 0.01837 0.00893 0.0043 1.0000 0.5671 -3.000 -0.3795 0.01757 0.00854 0.0078 1.0000 0.6445 -2.750 -0.3630 0.01691 0.00822 0.0123 1.0000 0.7289 -2.500 -0.3418 0.01650 0.00807 0.0168 1.0000 0.8213 -2.250 -0.2490 0.01679 0.00803 0.0087 1.0000 0.9365 -2.000 -0.1352 0.01604 0.00668 -0.0092 1.0000 1.0000 -1.750 -0.1253 0.01541 0.00596 -0.0083 1.0000 1.0000 -1.500 -0.1117 0.01500 0.00543 -0.0071 1.0000 1.0000 -1.250 -0.0955 0.01474 0.00506 -0.0059 1.0000 1.0000 -1.000 -0.0775 0.01456 0.00480 -0.0048 1.0000 1.0000 -0.750 -0.0586 0.01445 0.00461 -0.0036 1.0000 1.0000 -0.500 -0.0392 0.01438 0.00448 -0.0025 1.0000 1.0000 -0.250 -0.0197 0.01434 0.00440 -0.0012 1.0000 1.0000 0.000 0.0000 0.01432 0.00438 0.0000 1.0000 1.0000 0.250 0.0197 0.01434 0.00440 0.0012 1.0000 1.0000 0.500 0.0392 0.01438 0.00448 0.0025 1.0000 1.0000 0.750 0.0586 0.01445 0.00461 0.0036 1.0000 1.0000 1.000 0.0775 0.01456 0.00480 0.0048 1.0000 1.0000 1.250 0.0954 0.01474 0.00506 0.0059 1.0000 1.0000 1.500 0.1117 0.01500 0.00543 0.0071 1.0000 1.0000 1.750 0.1253 0.01541 0.00596 0.0083 1.0000 1.0000 2.000 0.1352 0.01603 0.00667 0.0092 1.0000 1.0000 2.250 0.2489 0.01679 0.00803 -0.0087 0.9366 1.0000 2.500 0.3418 0.01650 0.00807 -0.0168 0.8213 1.0000 2.750 0.3631 0.01691 0.00822 -0.0123 0.7289 1.0000 3.000 0.3796 0.01757 0.00854 -0.0078 0.6445 1.0000 3.250 0.3980 0.01837 0.00893 -0.0043 0.5671 1.0000 3.500 0.4182 0.01927 0.00946 -0.0017 0.4964 1.0000 3.750 0.4398 0.02026 0.01018 0.0003 0.4323 1.0000 4.000 0.4626 0.02136 0.01101 0.0019 0.3787 1.0000 4.250 0.4859 0.02254 0.01207 0.0032 0.3330 1.0000 4.500 0.5098 0.02389 0.01321 0.0044 0.2974 1.0000 4.750 0.5337 0.02530 0.01465 0.0054 0.2648 1.0000 5.000 0.5580 0.02693 0.01619 0.0064 0.2403 1.0000 5.250 0.5821 0.02878 0.01835 0.0072 0.2181 1.0000 5.500 0.6057 0.03058 0.02018 0.0081 0.1991 1.0000 5.750 0.6288 0.03282 0.02254 0.0089 0.1837 1.0000 6.000 0.6506 0.03515 0.02517 0.0097 0.1691 1.0000 6.250 0.6702 0.03888 0.02966 0.0101 0.1620 1.0000 6.500 0.6893 0.04193 0.03293 0.0107 0.1533 1.0000 6.750 0.7045 0.04582 0.03737 0.0107 0.1466 1.0000 7.000 0.7153 0.05122 0.04331 0.0100 0.1467 1.0000 7.250 0.7194 0.05792 0.05049 0.0079 0.1506 1.0000 7.500 0.7270 0.06368 0.05643 0.0066 0.1544 1.0000 7.750 0.6115 0.09127 0.08416 -0.0347 0.3614 1.0000 8.000 0.6440 0.09645 0.08948 -0.0324 0.3397 1.0000