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NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M24 AIRFOIL (m24-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.88 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m24-il-1000000-n5.txt
Download as CSV file: xf-m24-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M24 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3750   0.11171   0.10875   0.0098   0.5747   0.0119
  -9.500  -0.3702   0.10827   0.10530   0.0081   0.5717   0.0122
  -9.250  -0.3810   0.10082   0.09786   0.0042   0.5703   0.0133
  -9.000  -0.3742   0.09817   0.09520   0.0027   0.5673   0.0135
  -8.750  -0.3673   0.09554   0.09258   0.0011   0.5639   0.0135
  -8.500  -0.3602   0.09296   0.08999  -0.0007   0.5602   0.0137
  -8.250  -0.3548   0.09010   0.08712  -0.0030   0.5567   0.0138
  -8.000  -0.3515   0.08705   0.08406  -0.0055   0.5537   0.0139
  -7.750  -0.3476   0.08414   0.08114  -0.0072   0.5511   0.0141
  -7.500  -0.3392   0.08082   0.07779  -0.0097   0.5481   0.0143
  -7.250  -0.3296   0.07737   0.07431  -0.0121   0.5448   0.0146
  -7.000  -0.3187   0.07376   0.07065  -0.0146   0.5415   0.0149
  -6.750  -0.3145   0.06539   0.06215  -0.0196   0.5396   0.0163
  -6.500  -0.2986   0.06262   0.05932  -0.0210   0.5365   0.0164
  -6.250  -0.2807   0.06030   0.05696  -0.0220   0.5333   0.0165
  -6.000  -0.2619   0.05797   0.05457  -0.0230   0.5298   0.0167
  -5.750  -0.2426   0.05557   0.05209  -0.0239   0.5261   0.0168
  -5.250  -0.2023   0.05033   0.04668  -0.0256   0.5194   0.0173
  -5.000  -0.1813   0.04753   0.04378  -0.0262   0.5163   0.0176
  -4.750  -0.1598   0.04461   0.04075  -0.0267   0.5129   0.0182
  -4.500  -0.1388   0.04064   0.03660  -0.0268   0.5096   0.0187
  -4.250  -0.1191   0.03549   0.03118  -0.0262   0.5066   0.0192
  -4.000  -0.1023   0.02893   0.02425  -0.0246   0.5045   0.0199
  -3.500  -0.0643   0.01865   0.01311  -0.0214   0.4989   0.0208
  -3.250  -0.0397   0.01651   0.01062  -0.0207   0.4952   0.0211
  -3.000  -0.0132   0.01527   0.00911  -0.0204   0.4913   0.0213
  -2.750   0.0143   0.01435   0.00802  -0.0203   0.4879   0.0215
  -2.500   0.0422   0.01362   0.00713  -0.0203   0.4844   0.0217
  -2.250   0.0705   0.01304   0.00641  -0.0203   0.4806   0.0219
  -2.000   0.0989   0.01262   0.00588  -0.0204   0.4765   0.0222
  -1.750   0.1275   0.01223   0.00540  -0.0205   0.4729   0.0225
  -1.500   0.1561   0.01183   0.00493  -0.0206   0.4693   0.0227
  -1.250   0.1847   0.01150   0.00454  -0.0208   0.4657   0.0229
  -1.000   0.2133   0.01125   0.00422  -0.0209   0.4618   0.0231
  -0.750   0.2418   0.01104   0.00396  -0.0211   0.4580   0.0233
  -0.500   0.2704   0.01086   0.00375  -0.0212   0.4544   0.0235
  -0.250   0.2985   0.01055   0.00340  -0.0213   0.4505   0.0238
   0.000   0.3264   0.01029   0.00312  -0.0213   0.4468   0.0242
   0.250   0.3544   0.01014   0.00295  -0.0214   0.4431   0.0245
   0.500   0.3826   0.01000   0.00281  -0.0215   0.4400   0.0248
   0.750   0.4108   0.00989   0.00270  -0.0216   0.4361   0.0251
   1.000   0.4389   0.00981   0.00260  -0.0217   0.4318   0.0255
   1.250   0.4670   0.00975   0.00252  -0.0219   0.4278   0.0259
   1.500   0.4951   0.00967   0.00245  -0.0220   0.4249   0.0263
   1.750   0.5234   0.00962   0.00239  -0.0221   0.4215   0.0269
   2.000   0.5516   0.00959   0.00236  -0.0223   0.4177   0.0276
   2.250   0.5797   0.00958   0.00234  -0.0225   0.4136   0.0281
   2.500   0.6079   0.00956   0.00232  -0.0227   0.4100   0.0285
   2.750   0.6359   0.00952   0.00228  -0.0229   0.4063   0.0296
   3.000   0.6641   0.00953   0.00228  -0.0231   0.4025   0.0307
   3.250   0.6923   0.00956   0.00231  -0.0233   0.3988   0.0320
   3.500   0.7205   0.00959   0.00234  -0.0236   0.3955   0.0335
   3.750   0.7488   0.00960   0.00238  -0.0238   0.3925   0.0382
   4.000   0.7762   0.00955   0.00247  -0.0240   0.3888   0.0932
   4.250   0.8040   0.00958   0.00256  -0.0242   0.3847   0.1250
   4.500   0.8316   0.00961   0.00268  -0.0244   0.3807   0.1769
   4.750   0.8526   0.00895   0.00281  -0.0235   0.3779   0.5932
   5.000   0.8651   0.00806   0.00295  -0.0202   0.3751   0.9409
   5.250   0.8935   0.00821   0.00312  -0.0204   0.3716   0.9591
   5.500   0.9252   0.00845   0.00335  -0.0214   0.3680   0.9733
   5.750   0.9610   0.00865   0.00355  -0.0234   0.3647   0.9771
   6.000   0.9968   0.00888   0.00379  -0.0254   0.3617   0.9837
   6.250   1.0389   0.00908   0.00398  -0.0289   0.3578   0.9847
   6.500   1.0692   0.00926   0.00413  -0.0299   0.3522   0.9851
   6.750   1.0989   0.00942   0.00428  -0.0307   0.3447   0.9855
   7.000   1.1280   0.00964   0.00445  -0.0315   0.3368   0.9860
   7.250   1.1574   0.00980   0.00462  -0.0323   0.3321   0.9864
   7.500   1.1864   0.00998   0.00480  -0.0331   0.3256   0.9869
   7.750   1.2147   0.01024   0.00502  -0.0338   0.3170   0.9875
   8.000   1.2425   0.01054   0.00528  -0.0344   0.3060   0.9882
   8.250   1.2698   0.01086   0.00555  -0.0350   0.2933   0.9889
   8.500   1.2963   0.01122   0.00587  -0.0355   0.2801   0.9898
   8.750   1.3214   0.01171   0.00627  -0.0359   0.2629   0.9908
   9.000   1.3425   0.01258   0.00696  -0.0359   0.2306   0.9922
   9.250   1.3491   0.01496   0.00883  -0.0349   0.1512   0.9944
   9.500   1.3497   0.01813   0.01158  -0.0347   0.0751   0.9971
   9.750   1.3471   0.02064   0.01399  -0.0339   0.0452   1.0000
  10.000   1.3232   0.02289   0.01619  -0.0283   0.0273   1.0000
  10.250   1.3157   0.02475   0.01806  -0.0251   0.0201   1.0000
  10.500   1.3161   0.02634   0.01969  -0.0230   0.0179   1.0000
  10.750   1.3179   0.02802   0.02141  -0.0214   0.0162   1.0000
  11.000   1.3217   0.02967   0.02310  -0.0200   0.0153   1.0000
  11.250   1.3254   0.03147   0.02494  -0.0190   0.0145   1.0000
  11.500   1.3282   0.03344   0.02696  -0.0180   0.0137   1.0000
  11.750   1.3304   0.03555   0.02912  -0.0172   0.0129   1.0000
  12.000   1.3338   0.03762   0.03123  -0.0166   0.0124   1.0000
  12.250   1.3371   0.03972   0.03339  -0.0160   0.0121   1.0000
  12.500   1.3400   0.04191   0.03564  -0.0155   0.0117   1.0000
  12.750   1.3423   0.04421   0.03800  -0.0151   0.0113   1.0000
  13.000   1.3439   0.04668   0.04053  -0.0148   0.0110   1.0000
  13.250   1.3450   0.04928   0.04317  -0.0146   0.0106   1.0000
  13.500   1.3456   0.05196   0.04591  -0.0144   0.0103   1.0000
  13.750   1.3450   0.05481   0.04882  -0.0142   0.0099   1.0000
  14.000   1.3445   0.05774   0.05181  -0.0142   0.0096   1.0000
  14.250   1.3460   0.06045   0.05458  -0.0142   0.0094   1.0000
  14.500   1.3475   0.06315   0.05735  -0.0142   0.0092   1.0000
  14.750   1.3478   0.06608   0.06033  -0.0143   0.0090   1.0000
  15.000   1.3486   0.06894   0.06326  -0.0144   0.0087   1.0000
  15.250   1.3484   0.07199   0.06636  -0.0146   0.0085   1.0000
  15.500   1.3477   0.07508   0.06951  -0.0148   0.0083   1.0000
  15.750   1.3471   0.07820   0.07270  -0.0151   0.0081   1.0000
  16.000   1.3455   0.08151   0.07606  -0.0155   0.0079   1.0000
  16.250   1.3445   0.08475   0.07935  -0.0158   0.0077   1.0000
  16.500   1.3411   0.08831   0.08298  -0.0163   0.0075   1.0000
  16.750   1.3382   0.09184   0.08657  -0.0168   0.0073   1.0000
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