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NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 66(2)-215 (naca662215-il)
Reynolds number: 500,000
Max Cl/Cd: 72.9 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca662215-il-500000.txt
Download as CSV file: xf-naca662215-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(2)-215                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3611   0.08895   0.08659  -0.0757   0.9330   0.0329
 -12.500  -0.4218   0.06901   0.06661  -0.0879   0.9350   0.0323
 -12.250  -0.4984   0.05508   0.05240  -0.0944   0.9313   0.0315
 -12.000  -0.5341   0.04925   0.04638  -0.0947   0.9243   0.0314
 -11.750  -0.5576   0.04535   0.04233  -0.0936   0.9169   0.0315
 -11.500  -0.5817   0.04176   0.03857  -0.0917   0.9097   0.0315
 -11.250  -0.5965   0.03920   0.03587  -0.0895   0.9027   0.0317
 -11.000  -0.7311   0.03891   0.03431  -0.0797   0.9020   0.0236
 -10.750  -0.7382   0.03699   0.03212  -0.0753   0.8950   0.0236
 -10.500  -0.7397   0.03495   0.02979  -0.0717   0.8887   0.0238
 -10.250  -0.7422   0.03453   0.02902  -0.0674   0.8831   0.0242
 -10.000  -0.7337   0.03168   0.02590  -0.0654   0.8787   0.0243
  -9.750  -0.7194   0.02936   0.02335  -0.0639   0.8746   0.0243
  -9.500  -0.6998   0.02669   0.02043  -0.0634   0.8714   0.0245
  -9.250  -0.6747   0.02457   0.01816  -0.0637   0.8688   0.0250
  -9.000  -0.6508   0.02337   0.01687  -0.0636   0.8660   0.0254
  -8.750  -0.6276   0.02251   0.01597  -0.0634   0.8628   0.0261
  -8.500  -0.6038   0.02169   0.01509  -0.0632   0.8596   0.0268
  -8.250  -0.5792   0.02086   0.01417  -0.0630   0.8567   0.0276
  -8.000  -0.5520   0.01992   0.01312  -0.0632   0.8541   0.0282
  -7.750  -0.5254   0.01916   0.01225  -0.0633   0.8517   0.0289
  -7.500  -0.5001   0.01856   0.01157  -0.0632   0.8492   0.0294
  -7.250  -0.4691   0.01753   0.01050  -0.0642   0.8470   0.0302
  -7.000  -0.4437   0.01645   0.00945  -0.0643   0.8445   0.0314
  -6.750  -0.4245   0.01595   0.00894  -0.0632   0.8417   0.0325
  -6.500  -0.4057   0.01555   0.00851  -0.0619   0.8391   0.0337
  -6.250  -0.3876   0.01515   0.00806  -0.0604   0.8368   0.0349
  -6.000  -0.3695   0.01481   0.00767  -0.0589   0.8344   0.0359
  -5.750  -0.3509   0.01443   0.00727  -0.0576   0.8320   0.0369
  -5.500  -0.3370   0.01379   0.00661  -0.0554   0.8292   0.0387
  -5.250  -0.3179   0.01342   0.00624  -0.0542   0.8268   0.0407
  -5.000  -0.2969   0.01313   0.00593  -0.0532   0.8246   0.0431
  -4.750  -0.2748   0.01289   0.00563  -0.0524   0.8226   0.0450
  -4.500  -0.2550   0.01250   0.00523  -0.0512   0.8206   0.0494
  -4.250  -0.2325   0.01230   0.00501  -0.0505   0.8187   0.0545
  -4.000  -0.2137   0.01186   0.00474  -0.0492   0.8167   0.0826
  -3.750  -0.2121   0.01046   0.00425  -0.0453   0.8140   0.2890
  -3.500  -0.2114   0.00897   0.00373  -0.0413   0.8113   0.5148
  -3.250  -0.1967   0.00847   0.00384  -0.0388   0.8093   0.6711
  -3.000  -0.1700   0.00857   0.00395  -0.0386   0.8079   0.7005
  -2.750  -0.1426   0.00873   0.00410  -0.0385   0.8065   0.7197
  -2.500  -0.1151   0.00896   0.00433  -0.0383   0.8052   0.7361
  -2.250  -0.0874   0.00925   0.00460  -0.0380   0.8039   0.7498
  -2.000  -0.0604   0.00953   0.00486  -0.0378   0.8023   0.7612
  -1.750  -0.0327   0.00982   0.00523  -0.0375   0.8008   0.7690
  -1.500  -0.0057   0.01001   0.00539  -0.0375   0.7992   0.7764
  -1.250   0.0220   0.01020   0.00563  -0.0373   0.7976   0.7813
  -1.000   0.0498   0.01037   0.00581  -0.0374   0.7961   0.7856
  -0.750   0.0777   0.01042   0.00584  -0.0376   0.7946   0.7889
  -0.500   0.1058   0.01044   0.00583  -0.0380   0.7930   0.7921
  -0.250   0.1339   0.01044   0.00582  -0.0383   0.7917   0.7943
   0.000   0.1624   0.01046   0.00585  -0.0386   0.7905   0.7960
   0.250   0.1913   0.01047   0.00584  -0.0390   0.7890   0.7974
   0.500   0.2201   0.01049   0.00585  -0.0394   0.7871   0.7986
   0.750   0.2467   0.01049   0.00589  -0.0395   0.7844   0.8001
   1.000   0.2740   0.01049   0.00590  -0.0397   0.7814   0.8019
   1.250   0.3023   0.01045   0.00587  -0.0400   0.7787   0.8035
   1.500   0.3311   0.01040   0.00583  -0.0405   0.7766   0.8051
   1.750   0.3604   0.01037   0.00579  -0.0410   0.7747   0.8066
   2.000   0.3909   0.01027   0.00566  -0.0417   0.7713   0.8080
   2.250   0.4171   0.01003   0.00546  -0.0414   0.7636   0.8095
   2.500   0.4476   0.00977   0.00517  -0.0418   0.7581   0.8108
   2.750   0.4742   0.00962   0.00507  -0.0416   0.7509   0.8122
   3.000   0.5038   0.00934   0.00476  -0.0417   0.7421   0.8136
   3.250   0.5295   0.00915   0.00462  -0.0412   0.7315   0.8152
   3.500   0.5558   0.00894   0.00443  -0.0408   0.7189   0.8168
   3.750   0.5811   0.00878   0.00427  -0.0403   0.7030   0.8186
   4.000   0.6059   0.00867   0.00417  -0.0397   0.6836   0.8206
   4.250   0.6291   0.00863   0.00410  -0.0388   0.6537   0.8226
   4.500   0.6354   0.00908   0.00405  -0.0346   0.5455   0.8251
   4.750   0.6272   0.01013   0.00455  -0.0280   0.4290   0.8279
   5.000   0.6163   0.01116   0.00509  -0.0210   0.3215   0.8311
   5.250   0.6046   0.01223   0.00567  -0.0142   0.2184   0.8351
   5.500   0.5959   0.01363   0.00646  -0.0084   0.1001   0.8391
   5.750   0.6034   0.01447   0.00704  -0.0055   0.0551   0.8420
   6.000   0.6193   0.01492   0.00749  -0.0037   0.0477   0.8445
   6.250   0.6347   0.01543   0.00800  -0.0020   0.0428   0.8473
   6.500   0.6511   0.01592   0.00854  -0.0004   0.0400   0.8504
   6.750   0.6684   0.01639   0.00904   0.0009   0.0379   0.8537
   7.250   0.6938   0.01781   0.01052   0.0049   0.0338   0.8603
   7.500   0.7104   0.01832   0.01110   0.0063   0.0326   0.8636
   7.750   0.7268   0.01887   0.01170   0.0077   0.0313   0.8676
   8.000   0.7428   0.01950   0.01234   0.0090   0.0299   0.8718
   8.250   0.7571   0.02017   0.01306   0.0106   0.0288   0.8757
   8.500   0.7686   0.02117   0.01408   0.0126   0.0276   0.8799
   8.750   0.7843   0.02214   0.01511   0.0140   0.0269   0.8843
   9.000   0.8033   0.02276   0.01579   0.0149   0.0264   0.8887
   9.250   0.8214   0.02341   0.01653   0.0160   0.0257   0.8929
   9.500   0.8401   0.02407   0.01726   0.0170   0.0249   0.8978
   9.750   0.8593   0.02476   0.01798   0.0177   0.0241   0.9031
  10.000   0.8779   0.02548   0.01876   0.0187   0.0234   0.9081
  10.250   0.8982   0.02629   0.01960   0.0194   0.0229   0.9138
  10.500   0.9440   0.02831   0.02164   0.0166   0.0219   0.9149
  10.750   0.9604   0.02915   0.02263   0.0179   0.0217   0.9214
  11.000   0.9759   0.03007   0.02372   0.0193   0.0214   0.9293
  11.250   0.9919   0.03122   0.02506   0.0207   0.0210   0.9378
  11.500   1.0098   0.03270   0.02675   0.0217   0.0208   0.9476
  11.750   1.0282   0.03457   0.02886   0.0223   0.0206   0.9596
  12.000   1.0481   0.03656   0.03110   0.0216   0.0202   0.9741
  12.250   1.0601   0.03849   0.03324   0.0221   0.0197   1.0000
  12.500   1.0654   0.04096   0.03593   0.0235   0.0195   1.0000
  12.750   1.0640   0.04393   0.03917   0.0255   0.0196   1.0000
  13.000   1.0566   0.04729   0.04281   0.0278   0.0197   1.0000
  13.250   1.0397   0.05165   0.04748   0.0305   0.0201   1.0000
  13.500   1.0248   0.05531   0.05137   0.0325   0.0202   1.0000
  13.750   1.0035   0.05986   0.05615   0.0342   0.0206   1.0000
  14.000   0.9836   0.06421   0.06069   0.0352   0.0208   1.0000
  14.250   0.9626   0.06898   0.06564   0.0356   0.0211   1.0000
  14.500   0.8449   0.07164   0.06876   0.0372   0.0228   1.0000
  14.750   0.8329   0.07620   0.07339   0.0360   0.0227   1.0000
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