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NACA 4421 (naca4421-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 4421 (naca4421-il)
Reynolds number: 100,000
Max Cl/Cd: 36.06 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca4421-il-100000.txt
Download as CSV file: xf-naca4421-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7343   0.07273   0.06697  -0.0629   1.0000   0.1401
 -11.250  -0.8137   0.06750   0.06164  -0.0578   1.0000   0.1388
 -11.000  -0.8853   0.06263   0.05653  -0.0512   1.0000   0.1381
 -10.750  -0.9303   0.05585   0.04914  -0.0492   0.9953   0.1396
 -10.500  -0.9221   0.05203   0.04493  -0.0507   0.9881   0.1430
 -10.250  -0.8770   0.05238   0.04550  -0.0536   0.9819   0.1471
 -10.000  -0.8704   0.04895   0.04156  -0.0542   0.9739   0.1517
  -9.750  -0.8439   0.04712   0.03958  -0.0560   0.9668   0.1560
  -9.500  -0.8117   0.04679   0.03932  -0.0574   0.9594   0.1607
  -9.250  -0.7970   0.04404   0.03595  -0.0580   0.9514   0.1666
  -9.000  -0.7619   0.04391   0.03608  -0.0595   0.9442   0.1710
  -8.750  -0.7343   0.04293   0.03493  -0.0605   0.9363   0.1771
  -8.500  -0.7022   0.04169   0.03353  -0.0624   0.9302   0.1829
  -8.250  -0.6772   0.04140   0.03331  -0.0623   0.9207   0.1879
  -8.000  -0.6418   0.03995   0.03144  -0.0648   0.9153   0.1954
  -7.750  -0.6213   0.03973   0.03140  -0.0637   0.9050   0.1995
  -7.500  -0.5838   0.03908   0.03062  -0.0659   0.8988   0.2066
  -7.250  -0.5597   0.03820   0.02958  -0.0659   0.8905   0.2123
  -7.000  -0.5283   0.03789   0.02934  -0.0667   0.8824   0.2180
  -6.750  -0.4867   0.03704   0.02816  -0.0694   0.8779   0.2265
  -6.500  -0.4712   0.03659   0.02784  -0.0676   0.8664   0.2310
  -6.250  -0.4319   0.03605   0.02727  -0.0697   0.8607   0.2386
  -6.000  -0.3866   0.03503   0.02605  -0.0728   0.8574   0.2474
  -5.750  -0.3770   0.03487   0.02598  -0.0700   0.8441   0.2519
  -5.500  -0.3347   0.03411   0.02508  -0.0724   0.8396   0.2613
  -5.250  -0.3124   0.03360   0.02451  -0.0717   0.8305   0.2680
  -5.000  -0.2819   0.03312   0.02411  -0.0721   0.8227   0.2761
  -4.750  -0.2373   0.03215   0.02299  -0.0747   0.8190   0.2876
  -4.500  -0.2196   0.03203   0.02299  -0.0731   0.8084   0.2952
  -4.250  -0.1856   0.03141   0.02224  -0.0740   0.8018   0.3076
  -4.000  -0.1396   0.03055   0.02150  -0.0767   0.7988   0.3218
  -3.750  -0.0903   0.02956   0.02057  -0.0799   0.7967   0.3378
  -3.500  -0.0892   0.03000   0.02094  -0.0756   0.7819   0.3477
  -3.250  -0.0427   0.02909   0.02015  -0.0782   0.7789   0.3653
  -3.000   0.0049   0.02818   0.01931  -0.0810   0.7764   0.3841
  -2.750   0.0077   0.02873   0.01982  -0.0771   0.7628   0.3955
  -2.500   0.0505   0.02800   0.01916  -0.0791   0.7589   0.4150
  -2.250   0.0963   0.02711   0.01836  -0.0815   0.7560   0.4361
  -2.000   0.1045   0.02754   0.01888  -0.0784   0.7439   0.4495
  -1.750   0.1410   0.02698   0.01840  -0.0793   0.7388   0.4718
  -1.500   0.1841   0.02620   0.01773  -0.0812   0.7355   0.4984
  -1.250   0.1979   0.02653   0.01816  -0.0789   0.7256   0.5200
  -1.000   0.2264   0.02623   0.01802  -0.0786   0.7187   0.5493
  -0.750   0.2676   0.02550   0.01742  -0.0799   0.7149   0.5889
  -0.500   0.3112   0.02479   0.01685  -0.0816   0.7120   0.6341
  -0.250   0.3033   0.02592   0.01820  -0.0759   0.6986   0.6617
   0.000   0.3405   0.02536   0.01777  -0.0762   0.6945   0.7094
   0.250   0.3826   0.02474   0.01724  -0.0770   0.6913   0.7571
   0.500   0.3726   0.02600   0.01873  -0.0706   0.6787   0.7891
   0.750   0.4075   0.02572   0.01849  -0.0703   0.6742   0.8337
   1.000   0.4583   0.02531   0.01804  -0.0724   0.6710   0.8723
   1.250   0.4664   0.02656   0.01939  -0.0692   0.6600   0.9070
   1.500   0.5319   0.02643   0.01915  -0.0751   0.6547   0.9339
   1.750   0.6168   0.02591   0.01843  -0.0844   0.6505   0.9506
   2.000   0.6711   0.02661   0.01913  -0.0902   0.6408   0.9687
   2.250   0.7456   0.02636   0.01876  -0.0988   0.6335   0.9827
   2.500   0.8275   0.02574   0.01793  -0.1085   0.6282   0.9936
   2.750   0.8309   0.02665   0.01894  -0.1060   0.6185   1.0000
   3.000   0.8413   0.02668   0.01889  -0.1035   0.6123   1.0000
   3.250   0.8746   0.02635   0.01840  -0.1045   0.6076   1.0000
   3.500   0.8390   0.02765   0.01980  -0.0946   0.5989   1.0000
   3.750   0.8504   0.02789   0.01998  -0.0920   0.5923   1.0000
   4.000   0.8924   0.02753   0.01946  -0.0941   0.5876   1.0000
   4.250   0.8693   0.02883   0.02084  -0.0860   0.5795   1.0000
   4.500   0.8774   0.02934   0.02132  -0.0828   0.5723   1.0000
   4.750   0.9246   0.02891   0.02075  -0.0856   0.5675   1.0000
   5.000   0.9165   0.03006   0.02193  -0.0800   0.5600   1.0000
   5.250   0.9185   0.03090   0.02279  -0.0760   0.5522   1.0000
   5.500   0.9686   0.03036   0.02213  -0.0792   0.5472   1.0000
   5.750   0.9727   0.03132   0.02312  -0.0756   0.5401   1.0000
   6.000   0.9665   0.03251   0.02435  -0.0706   0.5317   1.0000
   6.250   1.0210   0.03180   0.02353  -0.0743   0.5266   1.0000
   6.500   1.0261   0.03281   0.02456  -0.0710   0.5195   1.0000
   6.750   1.0135   0.03422   0.02604  -0.0652   0.5109   1.0000
   7.000   1.0778   0.03319   0.02488  -0.0702   0.5058   1.0000
   7.250   1.0670   0.03470   0.02647  -0.0648   0.4981   1.0000
   7.500   1.0588   0.03602   0.02784  -0.0597   0.4899   1.0000
   7.750   1.1389   0.03441   0.02609  -0.0668   0.4848   1.0000
   8.000   1.0909   0.03725   0.02908  -0.0565   0.4760   1.0000
   8.250   1.1130   0.03744   0.02926  -0.0556   0.4686   1.0000
   8.500   1.2242   0.03452   0.02605  -0.0666   0.4623   1.0000
   8.750   1.1309   0.03899   0.03084  -0.0508   0.4528   1.0000
   9.000   1.2114   0.03638   0.02804  -0.0566   0.4459   1.0000
   9.250   1.2129   0.03744   0.02914  -0.0532   0.4383   1.0000
   9.500   1.2034   0.03893   0.03072  -0.0487   0.4300   1.0000
   9.750   1.3028   0.03613   0.02763  -0.0573   0.4237   1.0000
  10.000   1.2226   0.04060   0.03243  -0.0445   0.4152   1.0000
  10.250   1.2641   0.03972   0.03148  -0.0457   0.4083   1.0000
  10.500   1.3007   0.03935   0.03104  -0.0465   0.4015   1.0000
  10.750   1.2541   0.04302   0.03493  -0.0391   0.3931   1.0000
  11.000   1.3456   0.03960   0.03123  -0.0451   0.3865   1.0000
  11.250   1.2802   0.04443   0.03636  -0.0363   0.3786   1.0000
  11.500   1.3111   0.04394   0.03582  -0.0362   0.3713   1.0000
  11.750   1.3406   0.04373   0.03555  -0.0362   0.3641   1.0000
  12.000   1.3002   0.04777   0.03979  -0.0309   0.3558   1.0000
  12.250   1.3918   0.04360   0.03531  -0.0355   0.3485   1.0000
  12.500   1.3078   0.05064   0.04274  -0.0276   0.3404   1.0000
  12.750   1.3984   0.04598   0.03775  -0.0312   0.3327   1.0000
  13.000   1.3297   0.05250   0.04460  -0.0252   0.3249   1.0000
  13.250   1.3874   0.04983   0.04174  -0.0264   0.3167   1.0000
  13.500   1.3505   0.05452   0.04663  -0.0230   0.3089   1.0000
  13.750   1.3873   0.05337   0.04534  -0.0230   0.3005   1.0000
  14.000   1.3659   0.05712   0.04922  -0.0208   0.2927   1.0000
  14.250   1.3891   0.05709   0.04911  -0.0202   0.2844   1.0000
  14.500   1.3789   0.06014   0.05224  -0.0187   0.2768   1.0000
  14.750   1.3814   0.06204   0.05415  -0.0177   0.2689   1.0000
  15.000   1.3944   0.06316   0.05523  -0.0170   0.2615   1.0000
  15.250   1.3557   0.06932   0.06159  -0.0157   0.2545   1.0000
  15.500   1.4194   0.06552   0.05751  -0.0158   0.2471   1.0000
  15.750   1.3045   0.08040   0.07292  -0.0150   0.2413   1.0000
  16.000   1.4273   0.06950   0.06151  -0.0144   0.2341   1.0000
  16.250   1.3383   0.08183   0.07428  -0.0141   0.2295   1.0000
  16.750   1.4067   0.07919   0.07139  -0.0130   0.2172   1.0000
  17.000   0.8222   0.18607   0.17927  -0.0542   0.1986   1.0000
  17.250   0.8199   0.19136   0.18459  -0.0570   0.1989   1.0000
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