XFOIL Version 6.96 Calculated polar for: NACA 0010-34 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.6268 0.09892 0.09201 -0.0221 1.0000 0.0366 -10.000 -0.6334 0.09270 0.08592 -0.0261 1.0000 0.0358 -9.750 -0.6445 0.08691 0.08013 -0.0298 1.0000 0.0352 -9.500 -0.6589 0.08181 0.07500 -0.0322 1.0000 0.0346 -9.250 -0.6752 0.07747 0.07059 -0.0328 1.0000 0.0341 -9.000 -0.6920 0.07371 0.06674 -0.0317 1.0000 0.0336 -8.750 -0.7057 0.06984 0.06269 -0.0302 1.0000 0.0330 -8.500 -0.7161 0.06597 0.05856 -0.0282 1.0000 0.0323 -8.250 -0.7237 0.06220 0.05442 -0.0257 1.0000 0.0316 -7.750 -0.7245 0.05576 0.04705 -0.0200 1.0000 0.0306 -7.500 -0.7190 0.05235 0.04331 -0.0176 1.0000 0.0305 -7.250 -0.7115 0.04913 0.03960 -0.0151 1.0000 0.0305 -7.000 -0.7025 0.04582 0.03598 -0.0127 1.0000 0.0311 -6.750 -0.6902 0.04294 0.03295 -0.0110 1.0000 0.0327 -6.500 -0.6756 0.04042 0.03009 -0.0090 1.0000 0.0345 -6.250 -0.6578 0.03785 0.02712 -0.0070 1.0000 0.0357 -6.000 -0.6361 0.03532 0.02419 -0.0054 1.0000 0.0367 -5.750 -0.6110 0.03302 0.02153 -0.0042 1.0000 0.0380 -5.500 -0.5858 0.03091 0.01922 -0.0032 1.0000 0.0416 -5.250 -0.5633 0.02925 0.01745 -0.0020 1.0000 0.0468 -5.000 -0.5418 0.02779 0.01565 -0.0002 1.0000 0.0508 -4.750 -0.5251 0.02628 0.01409 0.0018 1.0000 0.0586 -4.500 -0.5087 0.02494 0.01263 0.0038 1.0000 0.0716 -4.250 -0.4932 0.02329 0.01110 0.0059 1.0000 0.1005 -4.000 -0.4961 0.01980 0.00994 0.0103 1.0000 0.4326 -3.750 -0.4573 0.02138 0.01300 0.0180 1.0000 0.8392 -3.500 -0.4190 0.02175 0.01278 0.0172 1.0000 0.8696 -3.250 -0.3754 0.02187 0.01238 0.0146 1.0000 0.8885 -3.000 -0.3325 0.02185 0.01193 0.0116 1.0000 0.9058 -2.750 -0.2909 0.02174 0.01142 0.0085 1.0000 0.9220 -2.500 -0.2502 0.02159 0.01096 0.0055 1.0000 0.9371 -2.250 -0.2083 0.02139 0.01050 0.0020 1.0000 0.9508 -2.000 -0.1664 0.02116 0.01001 -0.0016 1.0000 0.9638 -1.750 -0.1246 0.02090 0.00957 -0.0053 1.0000 0.9763 -1.500 -0.0813 0.02060 0.00911 -0.0095 1.0000 0.9875 -1.250 -0.0379 0.02028 0.00868 -0.0137 1.0000 0.9981 -1.000 -0.0238 0.02010 0.00847 -0.0123 1.0000 1.0000 -0.750 -0.0169 0.01997 0.00833 -0.0094 1.0000 1.0000 -0.500 -0.0108 0.01988 0.00822 -0.0064 1.0000 1.0000 -0.250 -0.0052 0.01983 0.00816 -0.0032 1.0000 1.0000 0.000 0.0000 0.01981 0.00814 0.0000 1.0000 1.0000 0.250 0.0052 0.01983 0.00816 0.0032 1.0000 1.0000 0.500 0.0108 0.01988 0.00822 0.0064 1.0000 1.0000 0.750 0.0169 0.01997 0.00832 0.0095 1.0000 1.0000 1.000 0.0238 0.02009 0.00846 0.0123 1.0000 1.0000 1.250 0.0379 0.02028 0.00868 0.0137 0.9981 1.0000 1.500 0.0813 0.02060 0.00911 0.0095 0.9875 1.0000 1.750 0.1246 0.02090 0.00957 0.0053 0.9763 1.0000 2.000 0.1664 0.02115 0.01000 0.0016 0.9638 1.0000 2.250 0.2082 0.02138 0.01049 -0.0020 0.9509 1.0000 2.500 0.2502 0.02158 0.01095 -0.0055 0.9371 1.0000 2.750 0.2909 0.02174 0.01142 -0.0085 0.9221 1.0000 3.000 0.3325 0.02184 0.01193 -0.0116 0.9059 1.0000 3.250 0.3753 0.02186 0.01238 -0.0146 0.8885 1.0000 3.500 0.4191 0.02175 0.01277 -0.0172 0.8697 1.0000 3.750 0.4573 0.02138 0.01300 -0.0180 0.8392 1.0000 4.000 0.4962 0.01979 0.00994 -0.0103 0.4342 1.0000 4.250 0.4931 0.02329 0.01110 -0.0059 0.1005 1.0000 4.500 0.5087 0.02493 0.01263 -0.0038 0.0717 1.0000 4.750 0.5251 0.02628 0.01408 -0.0017 0.0586 1.0000 5.000 0.5418 0.02779 0.01565 0.0002 0.0508 1.0000 5.250 0.5632 0.02924 0.01744 0.0020 0.0468 1.0000 5.500 0.5857 0.03090 0.01921 0.0032 0.0416 1.0000 5.750 0.6109 0.03301 0.02152 0.0042 0.0380 1.0000 6.000 0.6360 0.03532 0.02418 0.0054 0.0366 1.0000 6.250 0.6578 0.03785 0.02711 0.0070 0.0357 1.0000 6.500 0.6756 0.04041 0.03009 0.0090 0.0345 1.0000 6.750 0.6902 0.04294 0.03294 0.0110 0.0327 1.0000 7.000 0.7025 0.04583 0.03598 0.0127 0.0311 1.0000 7.250 0.7115 0.04913 0.03960 0.0151 0.0305 1.0000 7.500 0.7191 0.05235 0.04331 0.0176 0.0305 1.0000 7.750 0.7245 0.05577 0.04706 0.0200 0.0306 1.0000 8.250 0.7239 0.06221 0.05443 0.0257 0.0316 1.0000 8.500 0.7162 0.06599 0.05858 0.0282 0.0323 1.0000 8.750 0.7059 0.06987 0.06271 0.0302 0.0330 1.0000 9.000 0.6923 0.07374 0.06677 0.0316 0.0336 1.0000 9.250 0.6755 0.07751 0.07063 0.0327 0.0341 1.0000 9.500 0.6593 0.08186 0.07505 0.0321 0.0346 1.0000 9.750 0.6450 0.08698 0.08020 0.0297 0.0352 1.0000 10.000 0.6340 0.09278 0.08600 0.0260 0.0359 1.0000 10.250 0.6275 0.09900 0.09209 0.0219 0.0366 1.0000 10.500 0.6242 0.10474 0.09780 0.0187 0.0375 1.0000 10.750 0.6228 0.10987 0.10298 0.0165 0.0383 1.0000 11.000 0.6243 0.11429 0.10737 0.0157 0.0393 1.0000