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NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 24112 (naca24112-jf)
Reynolds number: 500,000
Max Cl/Cd: 83.02 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca24112-jf-500000-n5.txt
Download as CSV file: xf-naca24112-jf-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 24112                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -1.0685   0.05345   0.05024  -0.0341   1.0000   0.0138
 -14.250  -1.0952   0.04715   0.04369  -0.0365   1.0000   0.0138
 -14.000  -1.1094   0.04328   0.03962  -0.0364   1.0000   0.0139
 -13.750  -1.1169   0.04049   0.03666  -0.0351   1.0000   0.0140
 -13.500  -1.1200   0.03828   0.03430  -0.0332   1.0000   0.0141
 -13.250  -1.1198   0.03645   0.03233  -0.0310   1.0000   0.0142
 -13.000  -1.1172   0.03486   0.03061  -0.0285   1.0000   0.0143
 -12.750  -1.1107   0.03336   0.02897  -0.0263   1.0000   0.0145
 -12.500  -1.1007   0.03190   0.02737  -0.0246   1.0000   0.0147
 -12.250  -1.0889   0.03048   0.02580  -0.0229   1.0000   0.0149
 -12.000  -1.0756   0.02910   0.02426  -0.0214   1.0000   0.0151
 -11.750  -1.0610   0.02777   0.02276  -0.0199   1.0000   0.0154
 -11.500  -1.0451   0.02650   0.02131  -0.0185   1.0000   0.0157
 -11.250  -1.0279   0.02531   0.01995  -0.0172   1.0000   0.0160
 -11.000  -1.0093   0.02424   0.01870  -0.0160   1.0000   0.0163
 -10.750  -0.9901   0.02323   0.01755  -0.0148   1.0000   0.0166
 -10.500  -0.9703   0.02238   0.01664  -0.0137   1.0000   0.0169
 -10.250  -0.9489   0.02171   0.01591  -0.0128   1.0000   0.0173
 -10.000  -0.9271   0.02106   0.01521  -0.0119   1.0000   0.0176
  -9.750  -0.9052   0.02039   0.01446  -0.0109   1.0000   0.0180
  -9.500  -0.8831   0.01972   0.01370  -0.0100   1.0000   0.0184
  -9.250  -0.8609   0.01905   0.01294  -0.0091   1.0000   0.0188
  -9.000  -0.8386   0.01840   0.01219  -0.0081   1.0000   0.0193
  -8.750  -0.8162   0.01779   0.01148  -0.0071   1.0000   0.0197
  -8.500  -0.7944   0.01715   0.01079  -0.0060   1.0000   0.0201
  -8.250  -0.7722   0.01665   0.01029  -0.0049   1.0000   0.0206
  -8.000  -0.7499   0.01625   0.00987  -0.0039   1.0000   0.0212
  -7.750  -0.7280   0.01586   0.00945  -0.0027   1.0000   0.0218
  -7.500  -0.6943   0.01535   0.00888  -0.0040   0.9939   0.0227
  -7.250  -0.6595   0.01484   0.00829  -0.0055   0.9833   0.0234
  -7.000  -0.6271   0.01429   0.00772  -0.0066   0.9706   0.0242
  -6.750  -0.5952   0.01387   0.00729  -0.0074   0.9555   0.0250
  -6.500  -0.5652   0.01352   0.00690  -0.0078   0.9359   0.0260
  -6.250  -0.5380   0.01321   0.00651  -0.0075   0.9116   0.0271
  -6.000  -0.5132   0.01291   0.00611  -0.0066   0.8844   0.0281
  -5.500  -0.4645   0.01243   0.00545  -0.0047   0.8276   0.0304
  -5.250  -0.4395   0.01224   0.00513  -0.0039   0.7990   0.0317
  -5.000  -0.4143   0.01206   0.00482  -0.0032   0.7712   0.0330
  -4.750  -0.3888   0.01186   0.00454  -0.0025   0.7445   0.0347
  -4.500  -0.3629   0.01173   0.00430  -0.0020   0.7176   0.0366
  -4.250  -0.3367   0.01161   0.00404  -0.0015   0.6912   0.0383
  -4.000  -0.3107   0.01143   0.00380  -0.0010   0.6675   0.0405
  -3.750  -0.2842   0.01132   0.00360  -0.0006   0.6431   0.0432
  -3.500  -0.2577   0.01122   0.00339  -0.0002   0.6192   0.0458
  -3.250  -0.2311   0.01110   0.00321   0.0001   0.5964   0.0489
  -3.000  -0.2042   0.01102   0.00304   0.0004   0.5752   0.0523
  -2.750  -0.1775   0.01092   0.00289   0.0007   0.5537   0.0568
  -2.500  -0.1504   0.01086   0.00275   0.0010   0.5329   0.0613
  -2.250  -0.1234   0.01077   0.00262   0.0012   0.5139   0.0673
  -2.000  -0.0962   0.01072   0.00250   0.0015   0.4962   0.0738
  -1.750  -0.0691   0.01065   0.00240   0.0017   0.4783   0.0825
  -1.500  -0.0420   0.01058   0.00231   0.0019   0.4618   0.0934
  -1.250  -0.0148   0.01051   0.00223   0.0021   0.4475   0.1076
  -1.000   0.0123   0.01043   0.00216   0.0023   0.4340   0.1283
  -0.750   0.0389   0.01029   0.00208   0.0025   0.4207   0.1662
  -0.500   0.0565   0.00898   0.00185   0.0039   0.4103   0.4883
  -0.250   0.0780   0.00845   0.00180   0.0051   0.4007   0.6310
   0.000   0.1007   0.00812   0.00181   0.0064   0.3912   0.7304
   0.250   0.1252   0.00798   0.00186   0.0074   0.3821   0.7953
   0.500   0.1509   0.00795   0.00193   0.0082   0.3730   0.8415
   0.750   0.1777   0.00799   0.00202   0.0088   0.3658   0.8739
   1.000   0.2054   0.00807   0.00211   0.0091   0.3579   0.8983
   1.250   0.2338   0.00819   0.00221   0.0093   0.3508   0.9177
   1.500   0.2631   0.00833   0.00233   0.0093   0.3437   0.9355
   1.750   0.2938   0.00850   0.00245   0.0090   0.3373   0.9477
   2.000   0.3224   0.00859   0.00251   0.0090   0.3312   0.9548
   2.250   0.3539   0.00872   0.00258   0.0082   0.3243   0.9586
   2.500   0.3862   0.00884   0.00267   0.0074   0.3189   0.9621
   2.750   0.4170   0.00895   0.00275   0.0068   0.3129   0.9665
   3.000   0.4466   0.00909   0.00284   0.0064   0.3067   0.9709
   3.250   0.4806   0.00921   0.00294   0.0051   0.3015   0.9730
   3.500   0.5146   0.00933   0.00303   0.0038   0.2954   0.9752
   3.750   0.5475   0.00949   0.00314   0.0026   0.2894   0.9777
   4.000   0.5791   0.00959   0.00325   0.0018   0.2842   0.9808
   4.250   0.6106   0.00973   0.00336   0.0010   0.2782   0.9835
   4.500   0.6445   0.00988   0.00348  -0.0004   0.2725   0.9850
   4.750   0.6780   0.01000   0.00361  -0.0017   0.2668   0.9868
   5.000   0.7105   0.01016   0.00374  -0.0028   0.2605   0.9889
   5.250   0.7424   0.01031   0.00389  -0.0038   0.2552   0.9912
   5.500   0.7736   0.01046   0.00404  -0.0047   0.2490   0.9934
   5.750   0.8060   0.01065   0.00420  -0.0058   0.2428   0.9949
   6.000   0.8387   0.01079   0.00437  -0.0070   0.2365   0.9964
   6.250   0.8707   0.01099   0.00455  -0.0081   0.2296   0.9981
   6.500   0.9026   0.01116   0.00473  -0.0092   0.2230   0.9996
   6.750   0.9280   0.01137   0.00493  -0.0089   0.2159   1.0000
   7.000   0.9510   0.01156   0.00512  -0.0081   0.2093   1.0000
   7.250   0.9735   0.01178   0.00533  -0.0072   0.2015   1.0000
   7.500   0.9961   0.01200   0.00556  -0.0063   0.1941   1.0000
   7.750   1.0180   0.01229   0.00581  -0.0053   0.1854   1.0000
   8.000   1.0403   0.01253   0.00606  -0.0044   0.1771   1.0000
   8.250   1.0619   0.01283   0.00635  -0.0034   0.1684   1.0000
   8.500   1.0833   0.01317   0.00666  -0.0024   0.1586   1.0000
   8.750   1.1048   0.01349   0.00698  -0.0015   0.1493   1.0000
   9.000   1.1257   0.01387   0.00734  -0.0004   0.1396   1.0000
   9.250   1.1460   0.01430   0.00774   0.0007   0.1293   1.0000
   9.500   1.1659   0.01477   0.00817   0.0018   0.1185   1.0000
   9.750   1.1858   0.01524   0.00862   0.0029   0.1082   1.0000
  10.000   1.2052   0.01575   0.00912   0.0041   0.0980   1.0000
  10.250   1.2241   0.01632   0.00966   0.0052   0.0882   1.0000
  10.500   1.2426   0.01693   0.01024   0.0064   0.0790   1.0000
  10.750   1.2607   0.01758   0.01087   0.0076   0.0706   1.0000
  11.250   1.2956   0.01893   0.01222   0.0099   0.0564   1.0000
  11.500   1.3122   0.01963   0.01294   0.0112   0.0511   1.0000
  12.000   1.3427   0.02115   0.01451   0.0139   0.0426   1.0000
  12.250   1.3545   0.02202   0.01541   0.0156   0.0391   1.0000
  12.500   1.3649   0.02283   0.01627   0.0176   0.0365   1.0000
  12.750   1.3727   0.02386   0.01733   0.0195   0.0340   1.0000
  13.000   1.3810   0.02495   0.01850   0.0211   0.0321   1.0000
  13.250   1.3883   0.02622   0.01985   0.0224   0.0303   1.0000
  13.500   1.3932   0.02784   0.02152   0.0234   0.0287   1.0000
  13.750   1.3980   0.02963   0.02341   0.0240   0.0274   1.0000
  14.000   1.4021   0.03169   0.02557   0.0241   0.0262   1.0000
  14.250   1.4037   0.03422   0.02819   0.0237   0.0250   1.0000
  14.500   1.4024   0.03731   0.03138   0.0229   0.0241   1.0000
  14.750   1.3992   0.04083   0.03501   0.0216   0.0234   1.0000
  15.000   1.3957   0.04454   0.03884   0.0202   0.0228   1.0000
  15.250   1.3890   0.04875   0.04319   0.0185   0.0222   1.0000
  15.500   1.3792   0.05343   0.04799   0.0166   0.0218   1.0000
  15.750   1.3665   0.05851   0.05319   0.0146   0.0214   1.0000
  16.000   1.3518   0.06388   0.05868   0.0126   0.0210   1.0000
  16.250   1.3355   0.06946   0.06438   0.0104   0.0208   1.0000
  16.500   1.3187   0.07519   0.07022   0.0082   0.0205   1.0000
  16.750   1.3017   0.08107   0.07620   0.0059   0.0202   1.0000
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