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NACA 4421 (naca4421-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 4421 (naca4421-il)
Reynolds number: 50,000
Max Cl/Cd: 15.25 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca4421-il-50000-n5.txt
Download as CSV file: xf-naca4421-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4421                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4075   0.11566   0.10740  -0.0488   1.0000   0.1334
 -11.500  -0.4198   0.11261   0.10440  -0.0480   1.0000   0.1358
 -11.000  -0.5237   0.09404   0.08593  -0.0525   1.0000   0.1426
 -10.750  -0.5145   0.09383   0.08577  -0.0510   0.9987   0.1447
 -10.500  -0.6914   0.06718   0.05862  -0.0654   0.9840   0.1485
 -10.250  -0.7371   0.06021   0.05115  -0.0657   0.9722   0.1514
 -10.000  -0.7296   0.05725   0.04796  -0.0669   0.9648   0.1553
  -9.750  -0.7097   0.05644   0.04716  -0.0669   0.9567   0.1589
  -9.500  -0.7015   0.05340   0.04375  -0.0680   0.9492   0.1641
  -9.250  -0.6928   0.05157   0.04175  -0.0670   0.9396   0.1680
  -9.000  -0.6615   0.05097   0.04117  -0.0685   0.9336   0.1728
  -8.750  -0.6539   0.04904   0.03893  -0.0674   0.9240   0.1779
  -8.500  -0.6277   0.04797   0.03778  -0.0684   0.9172   0.1829
  -8.250  -0.6055   0.04729   0.03707  -0.0683   0.9094   0.1879
  -8.000  -0.5905   0.04549   0.03485  -0.0680   0.9007   0.1944
  -7.750  -0.5524   0.04510   0.03460  -0.0700   0.8960   0.1997
  -7.500  -0.5410   0.04438   0.03377  -0.0680   0.8850   0.2046
  -7.250  -0.5126   0.04309   0.03220  -0.0692   0.8789   0.2115
  -7.000  -0.4920   0.04270   0.03187  -0.0682   0.8698   0.2163
  -6.750  -0.4666   0.04181   0.03082  -0.0685   0.8621   0.2230
  -6.500  -0.4313   0.04086   0.02973  -0.0703   0.8574   0.2301
  -6.250  -0.4185   0.04051   0.02939  -0.0681   0.8459   0.2351
  -6.000  -0.3870   0.03958   0.02820  -0.0692   0.8398   0.2435
  -5.750  -0.3637   0.03910   0.02775  -0.0686   0.8316   0.2496
  -5.500  -0.3396   0.03861   0.02723  -0.0682   0.8229   0.2571
  -5.250  -0.3036   0.03776   0.02622  -0.0698   0.8180   0.2667
  -5.000  -0.2882   0.03759   0.02612  -0.0679   0.8073   0.2733
  -4.750  -0.2582   0.03699   0.02535  -0.0684   0.8005   0.2841
  -4.500  -0.2194   0.03633   0.02478  -0.0700   0.7964   0.2943
  -4.250  -0.2092   0.03631   0.02469  -0.0674   0.7840   0.3034
  -4.000  -0.1757   0.03579   0.02423  -0.0682   0.7785   0.3148
  -3.750  -0.1360   0.03512   0.02348  -0.0700   0.7749   0.3295
  -3.500  -0.1296   0.03538   0.02381  -0.0668   0.7616   0.3382
  -3.250  -0.0940   0.03485   0.02326  -0.0678   0.7567   0.3535
  -3.000  -0.0728   0.03479   0.02320  -0.0668   0.7482   0.3672
  -2.750  -0.0502   0.03469   0.02316  -0.0660   0.7396   0.3809
  -2.500  -0.0133   0.03419   0.02266  -0.0672   0.7352   0.3995
  -2.250   0.0018   0.03439   0.02287  -0.0653   0.7252   0.4149
  -2.000   0.0276   0.03424   0.02280  -0.0649   0.7180   0.4328
  -1.750   0.0644   0.03375   0.02236  -0.0659   0.7139   0.4556
  -1.500   0.0747   0.03415   0.02285  -0.0634   0.7033   0.4733
  -1.250   0.1013   0.03399   0.02278  -0.0629   0.6967   0.4978
  -1.000   0.1373   0.03352   0.02242  -0.0636   0.6928   0.5279
  -0.750   0.1443   0.03413   0.02315  -0.0606   0.6822   0.5509
  -0.500   0.1696   0.03405   0.02318  -0.0598   0.6757   0.5833
  -0.250   0.2043   0.03362   0.02289  -0.0600   0.6719   0.6205
   0.250   0.2315   0.03450   0.02401  -0.0551   0.6551   0.6893
   0.500   0.2649   0.03414   0.02374  -0.0548   0.6513   0.7337
   1.000   0.2947   0.03539   0.02523  -0.0502   0.6350   0.8150
   1.250   0.3403   0.03521   0.02507  -0.0520   0.6312   0.8637
   1.500   0.4038   0.03486   0.02463  -0.0571   0.6285   0.9080
   2.000   0.4855   0.03654   0.02624  -0.0640   0.6119   0.9849
   2.250   0.5501   0.03607   0.02563  -0.0703   0.6087   1.0000
   2.500   0.4946   0.03819   0.02770  -0.0591   0.5952   1.0000
   2.750   0.5200   0.03810   0.02747  -0.0587   0.5903   1.0000
   3.000   0.5599   0.03759   0.02681  -0.0601   0.5872   1.0000
   3.250   0.5213   0.04041   0.02962  -0.0524   0.5731   1.0000
   3.500   0.5539   0.04017   0.02927  -0.0527   0.5689   1.0000
   3.750   0.5961   0.03953   0.02850  -0.0541   0.5660   1.0000
   4.250   0.5952   0.04263   0.03152  -0.0483   0.5476   1.0000
   4.500   0.6379   0.04188   0.03067  -0.0494   0.5450   1.0000
   5.000   0.6365   0.04555   0.03432  -0.0444   0.5262   1.0000
   5.250   0.6791   0.04470   0.03338  -0.0453   0.5239   1.0000
   5.750   0.6767   0.04887   0.03756  -0.0408   0.5049   1.0000
   6.250   0.6777   0.05338   0.04209  -0.0375   0.4861   1.0000
   6.500   0.7158   0.05251   0.04117  -0.0376   0.4837   1.0000
   7.000   0.7147   0.05751   0.04621  -0.0348   0.4646   1.0000
   7.500   0.7160   0.06273   0.05148  -0.0326   0.4459   1.0000
   7.750   0.7507   0.06188   0.05059  -0.0323   0.4436   1.0000
   9.250   0.7507   0.07920   0.06811  -0.0281   0.3890   1.0000
   9.750   0.7525   0.08505   0.07403  -0.0274   0.3721   1.0000
  10.000   0.7812   0.08458   0.07357  -0.0267   0.3688   1.0000
  10.500   0.7833   0.09038   0.07944  -0.0262   0.3518   1.0000
  10.750   0.8159   0.08921   0.07826  -0.0253   0.3492   1.0000
  11.000   0.7880   0.09589   0.08502  -0.0258   0.3351   1.0000
  11.250   0.8193   0.09477   0.08391  -0.0249   0.3323   1.0000
  11.500   0.7945   0.10122   0.09043  -0.0257   0.3189   1.0000
  11.750   0.8236   0.10031   0.08954  -0.0248   0.3156   1.0000
  12.250   0.8280   0.10600   0.09531  -0.0249   0.2993   1.0000
  12.750   0.8321   0.11191   0.10130  -0.0254   0.2834   1.0000
  13.250   0.8358   0.11806   0.10755  -0.0262   0.2679   1.0000
  13.500   0.8532   0.11875   0.10825  -0.0259   0.2635   1.0000
  14.000   0.8631   0.12406   0.11365  -0.0267   0.2497   1.0000
  14.500   0.8607   0.13170   0.12138  -0.0287   0.2349   1.0000
  15.000   0.8571   0.13988   0.12964  -0.0314   0.2208   1.0000
  15.250   0.8801   0.13951   0.12929  -0.0307   0.2184   1.0000
  15.750   0.8718   0.14892   0.13878  -0.0343   0.2050   1.0000
  16.250   0.8638   0.15863   0.14857  -0.0385   0.1930   1.0000
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