XFOIL Version 6.96 Calculated polar for: WORTMANN FX 77-080 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -1.1038 0.09915 0.09689 0.0087 1.0000 0.0054 -15.750 -1.1727 0.08223 0.07983 -0.0008 1.0000 0.0052 -15.500 -1.2521 0.06176 0.05908 -0.0138 1.0000 0.0052 -15.250 -1.2937 0.04814 0.04518 -0.0252 1.0000 0.0051 -15.000 -1.3064 0.04235 0.03921 -0.0296 1.0000 0.0051 -14.750 -1.3171 0.03810 0.03479 -0.0316 1.0000 0.0051 -14.500 -1.3251 0.03497 0.03150 -0.0315 1.0000 0.0052 -14.250 -1.3326 0.03241 0.02877 -0.0300 1.0000 0.0052 -14.000 -1.3258 0.03119 0.02745 -0.0285 1.0000 0.0053 -13.750 -1.3235 0.02968 0.02581 -0.0261 1.0000 0.0054 -13.500 -1.3175 0.02816 0.02415 -0.0241 1.0000 0.0054 -13.250 -1.3065 0.02688 0.02275 -0.0225 1.0000 0.0055 -13.000 -1.2902 0.02605 0.02183 -0.0214 1.0000 0.0056 -12.750 -1.2774 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1.0000 6.500 0.7530 0.01044 0.00451 -0.0060 0.0168 1.0000 6.750 0.7755 0.01073 0.00482 -0.0049 0.0155 1.0000 7.000 0.7984 0.01099 0.00511 -0.0038 0.0146 1.0000 7.250 0.8212 0.01129 0.00543 -0.0028 0.0137 1.0000 7.500 0.8438 0.01162 0.00577 -0.0018 0.0127 1.0000 7.750 0.8662 0.01201 0.00619 -0.0007 0.0117 1.0000 8.000 0.8890 0.01237 0.00660 0.0003 0.0112 1.0000 8.250 0.9120 0.01272 0.00699 0.0012 0.0107 1.0000 8.500 0.9351 0.01307 0.00737 0.0021 0.0100 1.0000 8.750 0.9580 0.01346 0.00779 0.0030 0.0095 1.0000 9.000 0.9805 0.01392 0.00828 0.0039 0.0089 1.0000 9.250 1.0021 0.01451 0.00894 0.0050 0.0084 1.0000 9.500 1.0247 0.01496 0.00945 0.0059 0.0081 1.0000 9.750 1.0469 0.01547 0.01003 0.0068 0.0080 1.0000 10.000 1.0689 0.01601 0.01064 0.0077 0.0077 1.0000 10.250 1.0909 0.01653 0.01122 0.0086 0.0074 1.0000 10.500 1.1123 0.01712 0.01189 0.0096 0.0072 1.0000 10.750 1.1336 0.01772 0.01256 0.0105 0.0070 1.0000 11.000 1.1547 0.01833 0.01325 0.0114 0.0067 1.0000 11.250 1.1750 0.01903 0.01402 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