NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 50,000 Max Cl/Cd: 25.07 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034-il-50000-n5.txt Download as CSV file: xf-naca001034-il-50000-n5.csv |
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
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Polar data table (+)
Polar graphs
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