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NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 16-012 (naca16012-il)
Reynolds number: 500,000
Max Cl/Cd: 42.48 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca16012-il-500000.txt
Download as CSV file: xf-naca16012-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-012                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6737   0.08087   0.07852  -0.0536   1.0000   0.0159
 -11.750  -0.7026   0.07454   0.07213  -0.0557   1.0000   0.0157
 -11.500  -0.7317   0.06975   0.06725  -0.0551   1.0000   0.0155
 -11.250  -0.7607   0.06596   0.06338  -0.0526   1.0000   0.0154
 -11.000  -0.7892   0.06288   0.06021  -0.0485   1.0000   0.0153
 -10.750  -0.8183   0.06023   0.05746  -0.0430   1.0000   0.0151
 -10.500  -0.8480   0.05798   0.05511  -0.0362   1.0000   0.0149
 -10.250  -0.8786   0.05625   0.05328  -0.0282   1.0000   0.0148
 -10.000  -1.0090   0.04025   0.03611  -0.0048   0.9993   0.0126
  -9.750  -0.9418   0.04882   0.04540  -0.0117   0.9992   0.0140
  -9.500  -0.9668   0.03941   0.03520  -0.0052   0.9957   0.0136
  -9.250  -0.9563   0.03648   0.03193  -0.0035   0.9940   0.0142
  -9.000  -0.9494   0.03323   0.02827  -0.0004   0.9911   0.0147
  -8.750  -0.9369   0.02997   0.02456   0.0019   0.9888   0.0151
  -8.500  -0.9179   0.02767   0.02189   0.0031   0.9872   0.0156
  -8.250  -0.8943   0.02618   0.02012   0.0035   0.9859   0.0161
  -8.000  -0.8717   0.02352   0.01713   0.0039   0.9853   0.0170
  -7.750  -0.8442   0.02253   0.01608   0.0032   0.9844   0.0179
  -7.500  -0.8141   0.02214   0.01565   0.0021   0.9835   0.0192
  -7.250  -0.7971   0.02157   0.01500   0.0040   0.9799   0.0204
  -7.000  -0.7720   0.02092   0.01423   0.0043   0.9778   0.0215
  -6.750  -0.7460   0.01957   0.01273   0.0043   0.9766   0.0229
  -6.500  -0.7199   0.01862   0.01176   0.0041   0.9751   0.0247
  -6.250  -0.6910   0.01821   0.01133   0.0034   0.9737   0.0269
  -6.000  -0.6610   0.01786   0.01092   0.0025   0.9727   0.0291
  -5.750  -0.6345   0.01685   0.00982   0.0023   0.9717   0.0315
  -5.500  -0.6051   0.01627   0.00923   0.0015   0.9709   0.0347
  -5.250  -0.5945   0.01597   0.00890   0.0050   0.9653   0.0370
  -5.000  -0.5684   0.01568   0.00857   0.0050   0.9630   0.0393
  -4.750  -0.5434   0.01500   0.00784   0.0052   0.9611   0.0432
  -4.500  -0.5136   0.01464   0.00747   0.0044   0.9598   0.0478
  -4.250  -0.4826   0.01434   0.00713   0.0034   0.9588   0.0520
  -4.000  -0.4523   0.01395   0.00678   0.0025   0.9578   0.0630
  -3.750  -0.4439   0.01353   0.00653   0.0065   0.9519   0.0950
  -3.500  -0.4273   0.01258   0.00617   0.0082   0.9488   0.2245
  -3.250  -0.4137   0.01124   0.00574   0.0103   0.9464   0.4340
  -3.000  -0.4069   0.00977   0.00534   0.0145   0.9441   0.6743
  -2.750  -0.4020   0.00946   0.00546   0.0198   0.9381   0.7754
  -2.500  -0.3749   0.00944   0.00556   0.0201   0.9357   0.8241
  -2.250  -0.3440   0.00950   0.00564   0.0195   0.9341   0.8496
  -2.000  -0.3116   0.00959   0.00572   0.0186   0.9328   0.8677
  -1.750  -0.2794   0.00973   0.00587   0.0178   0.9316   0.8849
  -1.500  -0.2428   0.01000   0.00612   0.0161   0.9310   0.8966
  -1.250  -0.2057   0.01079   0.00692   0.0150   0.9306   0.9155
  -1.000  -0.1500   0.01163   0.00776   0.0094   0.9315   0.9188
  -0.750  -0.1063   0.01181   0.00791   0.0057   0.9313   0.9199
  -0.500  -0.0636   0.01191   0.00800   0.0022   0.9310   0.9210
  -0.250  -0.0526   0.01193   0.00800   0.0058   0.9253   0.9283
   0.000   0.0000   0.01198   0.00805   0.0000   0.9266   0.9266
   0.250   0.0525   0.01193   0.00800  -0.0058   0.9283   0.9253
   0.500   0.0636   0.01191   0.00800  -0.0022   0.9210   0.9310
   0.750   0.1063   0.01181   0.00791  -0.0057   0.9199   0.9313
   1.000   0.1500   0.01163   0.00776  -0.0094   0.9188   0.9315
   1.250   0.2052   0.01081   0.00695  -0.0150   0.9156   0.9306
   1.500   0.2428   0.01000   0.00612  -0.0161   0.8967   0.9310
   1.750   0.2793   0.00973   0.00586  -0.0178   0.8848   0.9317
   2.000   0.3115   0.00958   0.00572  -0.0185   0.8676   0.9328
   2.250   0.3440   0.00949   0.00564  -0.0195   0.8495   0.9341
   2.500   0.3748   0.00944   0.00556  -0.0201   0.8243   0.9357
   2.750   0.4019   0.00946   0.00546  -0.0197   0.7756   0.9381
   3.000   0.4070   0.00977   0.00534  -0.0145   0.6751   0.9441
   3.250   0.4136   0.01124   0.00574  -0.0103   0.4337   0.9464
   3.500   0.4273   0.01258   0.00616  -0.0082   0.2244   0.9488
   3.750   0.4437   0.01353   0.00653  -0.0064   0.0948   0.9520
   4.000   0.4523   0.01394   0.00677  -0.0025   0.0629   0.9578
   4.250   0.4826   0.01433   0.00712  -0.0034   0.0520   0.9588
   4.500   0.5136   0.01464   0.00747  -0.0044   0.0478   0.9598
   4.750   0.5434   0.01500   0.00784  -0.0053   0.0433   0.9612
   5.000   0.5684   0.01568   0.00857  -0.0050   0.0393   0.9631
   5.250   0.5945   0.01596   0.00889  -0.0050   0.0370   0.9653
   5.500   0.6052   0.01626   0.00923  -0.0015   0.0347   0.9709
   5.750   0.6345   0.01684   0.00981  -0.0024   0.0316   0.9717
   6.000   0.6611   0.01785   0.01091  -0.0025   0.0291   0.9727
   6.250   0.6911   0.01821   0.01133  -0.0034   0.0269   0.9738
   6.500   0.7201   0.01861   0.01175  -0.0042   0.0247   0.9751
   6.750   0.7462   0.01955   0.01271  -0.0044   0.0229   0.9766
   7.000   0.7721   0.02091   0.01422  -0.0043   0.0215   0.9779
   7.250   0.7970   0.02156   0.01498  -0.0040   0.0204   0.9800
   7.500   0.8141   0.02211   0.01562  -0.0021   0.0192   0.9835
   7.750   0.8441   0.02255   0.01611  -0.0032   0.0180   0.9844
   8.000   0.8718   0.02350   0.01711  -0.0039   0.0170   0.9853
   8.250   0.8944   0.02619   0.02013  -0.0035   0.0161   0.9859
   8.500   0.9181   0.02765   0.02188  -0.0031   0.0156   0.9872
   8.750   0.9372   0.02996   0.02456  -0.0019   0.0151   0.9889
   9.000   0.9497   0.03322   0.02826   0.0003   0.0147   0.9912
   9.250   0.9562   0.03654   0.03201   0.0035   0.0142   0.9941
   9.500   0.9687   0.03909   0.03484   0.0049   0.0136   0.9957
   9.750   0.9937   0.03886   0.03457   0.0041   0.0130   0.9973
  10.000   1.0099   0.04017   0.03603   0.0047   0.0126   0.9993
  10.250   0.8787   0.05626   0.05330   0.0282   0.0148   1.0000
  10.500   0.8478   0.05801   0.05514   0.0363   0.0149   1.0000
  10.750   0.8184   0.06020   0.05743   0.0430   0.0151   1.0000
  11.000   0.7892   0.06291   0.06024   0.0485   0.0152   1.0000
  11.250   0.7605   0.06600   0.06342   0.0526   0.0154   1.0000
  11.500   0.7314   0.06984   0.06735   0.0552   0.0155   1.0000
  11.750   0.7027   0.07453   0.07212   0.0557   0.0157   1.0000
  12.000   0.6737   0.08092   0.07858   0.0535   0.0159   1.0000
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