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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 84.6 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63209-il-1000000.txt
Download as CSV file: xf-naca63209-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5893   0.04395   0.04237  -0.0384   1.0000   0.0095
  -8.750  -0.6154   0.03993   0.03825  -0.0390   1.0000   0.0094
  -8.500  -0.6329   0.03358   0.03170  -0.0396   1.0000   0.0092
  -8.250  -0.6457   0.02607   0.02386  -0.0396   1.0000   0.0088
  -8.000  -0.6987   0.02337   0.01976  -0.0378   1.0000   0.0082
  -7.750  -0.6817   0.02044   0.01647  -0.0369   1.0000   0.0086
  -7.500  -0.6609   0.01890   0.01473  -0.0361   1.0000   0.0091
  -7.250  -0.6390   0.01790   0.01357  -0.0353   1.0000   0.0096
  -7.000  -0.6162   0.01749   0.01305  -0.0345   1.0000   0.0100
  -6.750  -0.5952   0.01433   0.00953  -0.0341   0.9987   0.0106
  -6.500  -0.5617   0.01340   0.00853  -0.0358   0.9947   0.0113
  -6.250  -0.5288   0.01274   0.00781  -0.0372   0.9900   0.0119
  -6.000  -0.4947   0.01206   0.00707  -0.0389   0.9854   0.0126
  -5.750  -0.4612   0.01145   0.00639  -0.0403   0.9793   0.0135
  -5.500  -0.4272   0.01126   0.00615  -0.0417   0.9716   0.0143
  -5.250  -0.3978   0.01007   0.00484  -0.0424   0.9603   0.0153
  -5.000  -0.3701   0.00945   0.00415  -0.0426   0.9474   0.0165
  -4.750  -0.3436   0.00912   0.00377  -0.0423   0.9340   0.0175
  -4.500  -0.3174   0.00885   0.00342  -0.0420   0.9213   0.0189
  -4.250  -0.2910   0.00869   0.00320  -0.0417   0.9093   0.0202
  -4.000  -0.2648   0.00829   0.00269  -0.0413   0.8977   0.0221
  -3.750  -0.2380   0.00799   0.00234  -0.0411   0.8863   0.0257
  -3.500  -0.2107   0.00783   0.00212  -0.0410   0.8753   0.0289
  -3.250  -0.1835   0.00756   0.00182  -0.0409   0.8646   0.0379
  -3.000  -0.1563   0.00729   0.00161  -0.0408   0.8542   0.0625
  -2.750  -0.1296   0.00670   0.00137  -0.0409   0.8436   0.1665
  -2.500  -0.1033   0.00591   0.00111  -0.0413   0.8332   0.3314
  -2.250  -0.0765   0.00537   0.00098  -0.0414   0.8233   0.4633
  -2.000  -0.0491   0.00515   0.00092  -0.0414   0.8133   0.5315
  -1.750  -0.0211   0.00503   0.00088  -0.0415   0.8033   0.5711
  -1.500   0.0069   0.00495   0.00085  -0.0415   0.7937   0.6029
  -1.250   0.0347   0.00489   0.00083  -0.0415   0.7842   0.6340
  -1.000   0.0627   0.00483   0.00083  -0.0415   0.7742   0.6643
  -0.750   0.0906   0.00480   0.00084  -0.0414   0.7648   0.6911
  -0.500   0.1186   0.00480   0.00083  -0.0414   0.7552   0.7061
  -0.250   0.1469   0.00480   0.00084  -0.0414   0.7452   0.7200
   0.000   0.1751   0.00481   0.00084  -0.0415   0.7353   0.7324
   0.250   0.2032   0.00483   0.00086  -0.0415   0.7253   0.7436
   0.500   0.2312   0.00484   0.00087  -0.0415   0.7144   0.7542
   0.750   0.2594   0.00486   0.00089  -0.0415   0.7025   0.7645
   1.000   0.2874   0.00489   0.00092  -0.0415   0.6893   0.7751
   1.250   0.3153   0.00493   0.00096  -0.0414   0.6749   0.7857
   1.500   0.3428   0.00499   0.00099  -0.0413   0.6522   0.7962
   1.750   0.3700   0.00509   0.00103  -0.0411   0.6231   0.8067
   2.000   0.3974   0.00520   0.00108  -0.0410   0.5974   0.8177
   2.250   0.4247   0.00530   0.00116  -0.0409   0.5727   0.8289
   2.500   0.4518   0.00542   0.00124  -0.0407   0.5447   0.8399
   2.750   0.4780   0.00565   0.00134  -0.0405   0.4962   0.8513
   3.000   0.5029   0.00608   0.00150  -0.0401   0.4152   0.8633
   3.250   0.5261   0.00681   0.00179  -0.0395   0.2930   0.8760
   3.500   0.5486   0.00764   0.00215  -0.0389   0.1717   0.8895
   3.750   0.5716   0.00831   0.00249  -0.0383   0.0856   0.9037
   4.000   0.5951   0.00877   0.00279  -0.0375   0.0427   0.9189
   4.250   0.6186   0.00902   0.00306  -0.0366   0.0316   0.9362
   4.500   0.6414   0.00931   0.00338  -0.0354   0.0239   0.9593
   4.750   0.6726   0.00955   0.00367  -0.0363   0.0211   1.0000
   5.000   0.7000   0.00988   0.00399  -0.0363   0.0188   1.0000
   5.250   0.7259   0.01046   0.00463  -0.0362   0.0167   1.0000
   5.500   0.7514   0.01107   0.00532  -0.0359   0.0158   1.0000
   5.750   0.7781   0.01142   0.00569  -0.0358   0.0151   1.0000
   6.000   0.8043   0.01181   0.00612  -0.0357   0.0142   1.0000
   6.250   0.8298   0.01233   0.00667  -0.0354   0.0135   1.0000
   6.500   0.8550   0.01286   0.00725  -0.0351   0.0128   1.0000
   6.750   0.8795   0.01351   0.00793  -0.0347   0.0123   1.0000
   7.000   0.9021   0.01449   0.00899  -0.0341   0.0118   1.0000
   7.250   0.9203   0.01672   0.01139  -0.0328   0.0110   1.0000
   7.500   0.9466   0.01691   0.01163  -0.0327   0.0107   1.0000
   7.750   0.9714   0.01748   0.01229  -0.0323   0.0102   1.0000
   8.000   0.9948   0.01844   0.01334  -0.0318   0.0098   1.0000
   8.250   1.0177   0.01947   0.01448  -0.0313   0.0094   1.0000
   8.500   1.0404   0.02046   0.01558  -0.0307   0.0090   1.0000
   8.750   1.0625   0.02148   0.01671  -0.0301   0.0087   1.0000
   9.000   1.0843   0.02239   0.01771  -0.0296   0.0084   1.0000
   9.250   1.1045   0.02356   0.01898  -0.0289   0.0081   1.0000
   9.500   1.1129   0.02757   0.02339  -0.0271   0.0076   1.0000
   9.750   1.1239   0.03023   0.02640  -0.0254   0.0073   1.0000
  10.000   1.1421   0.03119   0.02751  -0.0245   0.0070   1.0000
  10.250   1.1520   0.03354   0.03012  -0.0229   0.0067   1.0000
  10.500   1.1490   0.03760   0.03456  -0.0203   0.0065   1.0000
  10.750   1.1261   0.04336   0.04076  -0.0164   0.0064   1.0000
  11.000   1.0919   0.04846   0.04615  -0.0119   0.0064   1.0000
  11.250   1.0528   0.05493   0.05290  -0.0106   0.0064   1.0000
  11.500   1.0205   0.06164   0.05981  -0.0123   0.0065   1.0000
  11.750   0.9930   0.06898   0.06731  -0.0162   0.0066   1.0000
  12.000   0.9579   0.07973   0.07820  -0.0240   0.0068   1.0000
  12.250   0.8016   0.10564   0.10440  -0.0398   0.0082   1.0000
  12.500   0.8108   0.10747   0.10623  -0.0414   0.0080   1.0000
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