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NACA M17 AIRFOIL (m17-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M17 AIRFOIL (m17-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.29 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m17-il-1000000.txt
Download as CSV file: xf-m17-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M17 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5070   0.11128   0.10985   0.0167   1.0000   0.0121
  -9.250  -0.5003   0.10837   0.10695   0.0160   1.0000   0.0123
  -9.000  -0.4938   0.10540   0.10399   0.0146   0.9643   0.0125
  -8.750  -0.4934   0.10314   0.10149   0.0151   0.8758   0.0127
  -8.500  -0.4891   0.10022   0.09845   0.0139   0.8463   0.0129
  -8.250  -0.4848   0.09708   0.09522   0.0123   0.8249   0.0133
  -8.000  -0.4807   0.09379   0.09187   0.0103   0.8074   0.0138
  -7.500  -0.4716   0.08414   0.08211  -0.0016   0.7783   0.0154
  -7.250  -0.4610   0.07938   0.07726  -0.0056   0.7659   0.0155
  -7.000  -0.4488   0.07451   0.07231  -0.0093   0.7545   0.0155
  -6.750  -0.4349   0.06960   0.06731  -0.0127   0.7438   0.0156
  -6.500  -0.4269   0.06307   0.06066  -0.0160   0.7343   0.0159
  -6.250  -0.4099   0.06150   0.05903  -0.0164   0.7225   0.0163
  -6.000  -0.3911   0.05927   0.05673  -0.0176   0.7119   0.0168
  -5.750  -0.3708   0.05654   0.05390  -0.0192   0.7023   0.0178
  -5.000  -0.3038   0.03796   0.03460  -0.0250   0.6794   0.0207
  -4.750  -0.2815   0.03732   0.03391  -0.0252   0.6707   0.0212
  -4.500  -0.2581   0.03644   0.03295  -0.0255   0.6624   0.0220
  -3.750  -0.1862   0.02217   0.01754  -0.0237   0.6438   0.0270
  -3.500  -0.1609   0.02152   0.01685  -0.0239   0.6366   0.0278
  -3.250  -0.1350   0.02085   0.01608  -0.0239   0.6301   0.0285
  -3.000  -0.1087   0.01982   0.01492  -0.0238   0.6237   0.0296
  -2.750  -0.0819   0.01860   0.01350  -0.0235   0.6173   0.0315
  -2.500  -0.0515   0.01959   0.01443  -0.0234   0.6109   0.0342
  -2.250  -0.0247   0.01822   0.01282  -0.0230   0.6052   0.0343
  -2.000  -0.0008   0.01362   0.00772  -0.0222   0.6005   0.0321
  -1.750   0.0269   0.01227   0.00616  -0.0219   0.5948   0.0311
  -1.500   0.0548   0.01135   0.00508  -0.0218   0.5889   0.0306
  -1.250   0.0827   0.01072   0.00435  -0.0217   0.5835   0.0306
  -1.000   0.1107   0.01027   0.00384  -0.0216   0.5779   0.0311
  -0.750   0.1385   0.00983   0.00332  -0.0215   0.5724   0.0315
  -0.500   0.1664   0.00947   0.00294  -0.0214   0.5670   0.0321
  -0.250   0.1942   0.00920   0.00263  -0.0214   0.5612   0.0327
   0.000   0.2221   0.00900   0.00239  -0.0213   0.5560   0.0332
   0.250   0.2501   0.00879   0.00217  -0.0213   0.5506   0.0336
   0.500   0.2781   0.00864   0.00198  -0.0213   0.5451   0.0338
   0.750   0.3061   0.00850   0.00182  -0.0214   0.5397   0.0341
   1.000   0.3343   0.00837   0.00169  -0.0214   0.5342   0.0345
   1.250   0.3622   0.00822   0.00147  -0.0214   0.5288   0.0363
   1.500   0.3905   0.00811   0.00137  -0.0215   0.5236   0.0390
   1.750   0.4188   0.00806   0.00132  -0.0216   0.5180   0.0425
   2.000   0.4470   0.00803   0.00130  -0.0217   0.5127   0.0535
   2.250   0.4745   0.00774   0.00137  -0.0217   0.5069   0.1917
   2.500   0.4884   0.00585   0.00150  -0.0189   0.5010   0.9658
   2.750   0.5381   0.00600   0.00163  -0.0238   0.4926   0.9899
   3.000   0.6013   0.00622   0.00178  -0.0318   0.4824   0.9984
   3.250   0.6384   0.00630   0.00183  -0.0339   0.4740   1.0000
   3.500   0.6650   0.00636   0.00187  -0.0338   0.4685   1.0000
   3.750   0.6916   0.00640   0.00192  -0.0336   0.4629   1.0000
   4.000   0.7179   0.00648   0.00197  -0.0333   0.4568   1.0000
   4.250   0.7443   0.00654   0.00203  -0.0331   0.4504   1.0000
   4.500   0.7705   0.00664   0.00211  -0.0329   0.4403   1.0000
   4.750   0.7968   0.00672   0.00218  -0.0327   0.4299   1.0000
   5.000   0.8229   0.00682   0.00226  -0.0324   0.4188   1.0000
   5.250   0.8488   0.00696   0.00236  -0.0322   0.4026   1.0000
   5.500   0.8744   0.00715   0.00249  -0.0319   0.3835   1.0000
   5.750   0.8998   0.00737   0.00264  -0.0316   0.3579   1.0000
   6.000   0.9241   0.00784   0.00289  -0.0313   0.3081   1.0000
   6.250   0.9456   0.00888   0.00345  -0.0309   0.2156   1.0000
   6.500   0.9659   0.01004   0.00415  -0.0303   0.1301   1.0000
   6.750   0.9824   0.01172   0.00525  -0.0293   0.0251   1.0000
   7.000   1.0051   0.01224   0.00575  -0.0286   0.0190   1.0000
   7.250   1.0286   0.01259   0.00613  -0.0280   0.0175   1.0000
   7.500   1.0517   0.01300   0.00659  -0.0274   0.0160   1.0000
   7.750   1.0734   0.01360   0.00723  -0.0266   0.0144   1.0000
   8.000   1.0945   0.01424   0.00795  -0.0258   0.0135   1.0000
   8.250   1.1168   0.01469   0.00843  -0.0251   0.0129   1.0000
   8.500   1.1387   0.01517   0.00895  -0.0244   0.0121   1.0000
   8.750   1.1600   0.01572   0.00954  -0.0237   0.0114   1.0000
   9.000   1.1798   0.01642   0.01029  -0.0228   0.0108   1.0000
   9.250   1.1920   0.01789   0.01187  -0.0210   0.0100   1.0000
   9.500   1.2094   0.01873   0.01279  -0.0199   0.0098   1.0000
   9.750   1.2277   0.01945   0.01357  -0.0189   0.0095   1.0000
  10.000   1.2441   0.02030   0.01449  -0.0178   0.0092   1.0000
  10.250   1.2586   0.02125   0.01551  -0.0164   0.0089   1.0000
  10.500   1.2712   0.02226   0.01659  -0.0149   0.0086   1.0000
  10.750   1.2805   0.02325   0.01765  -0.0130   0.0083   1.0000
  11.000   1.2897   0.02432   0.01878  -0.0115   0.0080   1.0000
  11.250   1.2998   0.02553   0.02003  -0.0105   0.0078   1.0000
  11.500   1.3067   0.02717   0.02172  -0.0097   0.0075   1.0000
  11.750   1.3075   0.02951   0.02416  -0.0086   0.0073   1.0000
  12.000   1.2980   0.03298   0.02776  -0.0063   0.0070   1.0000
  12.250   1.3079   0.03456   0.02944  -0.0061   0.0069   1.0000
  12.500   1.3156   0.03639   0.03137  -0.0057   0.0068   1.0000
  12.750   1.3218   0.03841   0.03349  -0.0052   0.0067   1.0000
  13.000   1.3264   0.04061   0.03580  -0.0048   0.0066   1.0000
  13.250   1.3298   0.04297   0.03827  -0.0043   0.0065   1.0000
  13.500   1.3320   0.04550   0.04092  -0.0040   0.0064   1.0000
  13.750   1.3328   0.04821   0.04375  -0.0037   0.0063   1.0000
  14.000   1.3323   0.05112   0.04680  -0.0035   0.0062   1.0000
  14.250   1.3305   0.05422   0.05004  -0.0035   0.0061   1.0000
  14.500   1.3267   0.05763   0.05359  -0.0036   0.0060   1.0000
  14.750   1.3216   0.06127   0.05736  -0.0040   0.0060   1.0000
  15.000   1.3154   0.06516   0.06139  -0.0046   0.0059   1.0000
  15.250   1.3083   0.06938   0.06575  -0.0056   0.0058   1.0000
  15.500   1.3001   0.07391   0.07042  -0.0068   0.0058   1.0000
  15.750   1.2888   0.07905   0.07572  -0.0084   0.0057   1.0000
  16.000   1.2780   0.08436   0.08117  -0.0103   0.0057   1.0000
  16.250   1.2654   0.09014   0.08709  -0.0126   0.0056   1.0000
  16.500   1.2515   0.09634   0.09344  -0.0152   0.0056   1.0000
  16.750   1.2338   0.10349   0.10076  -0.0183   0.0056   1.0000
  17.000   1.2145   0.11126   0.10869  -0.0220   0.0056   1.0000
  17.250   1.1919   0.12004   0.11764  -0.0264   0.0056   1.0000
  17.500   1.1647   0.13042   0.12821  -0.0319   0.0057   1.0000
  17.750   1.1312   0.14313   0.14114  -0.0390   0.0058   1.0000
  18.000   1.0914   0.15898   0.15719  -0.0481   0.0060   1.0000
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