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GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GRUMMAN K-2 AIRFOIL (k2-il)
Reynolds number: 100,000
Max Cl/Cd: 28.89 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k2-il-100000.txt
Download as CSV file: xf-k2-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GRUMMAN K-2 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5959   0.09809   0.09254  -0.0202   1.0000   0.1570
  -8.250  -0.5994   0.09465   0.08914  -0.0207   1.0000   0.1635
  -8.000  -0.7011   0.08803   0.08269  -0.0279   1.0000   0.1677
  -7.750  -0.6146   0.08657   0.08120  -0.0217   1.0000   0.1753
  -7.500  -0.6566   0.08150   0.07623  -0.0241   1.0000   0.1819
  -7.000  -0.6749   0.07469   0.06953  -0.0213   1.0000   0.1935
  -6.750  -0.7200   0.07009   0.06485  -0.0222   1.0000   0.2041
  -6.500  -0.7653   0.04938   0.04199  -0.0273   1.0000   0.0931
  -6.250  -0.7488   0.04352   0.03561  -0.0260   1.0000   0.0768
  -6.000  -0.7325   0.03953   0.03126  -0.0251   1.0000   0.0728
  -5.750  -0.7119   0.03650   0.02721  -0.0239   1.0000   0.0682
  -5.500  -0.6909   0.03354   0.02403  -0.0234   1.0000   0.0690
  -5.250  -0.6688   0.03145   0.02190  -0.0228   1.0000   0.0708
  -5.000  -0.6454   0.02963   0.01990  -0.0220   1.0000   0.0721
  -4.750  -0.6211   0.02786   0.01793  -0.0211   1.0000   0.0729
  -4.500  -0.5967   0.02633   0.01624  -0.0202   1.0000   0.0745
  -4.250  -0.5721   0.02509   0.01483  -0.0192   1.0000   0.0775
  -4.000  -0.5487   0.02365   0.01344  -0.0182   1.0000   0.0820
  -3.750  -0.5250   0.02257   0.01242  -0.0172   1.0000   0.0873
  -3.500  -0.5011   0.02146   0.01134  -0.0162   1.0000   0.0935
  -3.250  -0.4768   0.02046   0.01045  -0.0157   1.0000   0.1044
  -3.000  -0.4511   0.01932   0.00947  -0.0155   1.0000   0.1207
  -2.750  -0.4211   0.01728   0.00826  -0.0170   1.0000   0.2040
  -2.500  -0.4227   0.01649   0.01017  -0.0082   1.0000   0.6859
  -2.250  -0.4122   0.01788   0.01148  -0.0021   1.0000   0.7378
  -2.000  -0.4012   0.01905   0.01255   0.0035   1.0000   0.7682
  -1.750  -0.3952   0.02003   0.01349   0.0105   1.0000   0.7884
  -1.500  -0.3881   0.02078   0.01420   0.0170   1.0000   0.8093
  -1.250  -0.3822   0.02145   0.01483   0.0237   1.0000   0.8369
  -1.000  -0.3796   0.02184   0.01520   0.0315   1.0000   0.8669
  -0.750  -0.3702   0.02172   0.01503   0.0379   1.0000   0.8967
  -0.500  -0.3449   0.02131   0.01453   0.0396   1.0000   0.9171
  -0.250  -0.3182   0.02085   0.01397   0.0399   1.0000   0.9313
   0.000  -0.2847   0.02043   0.01346   0.0387   1.0000   0.9453
   0.250  -0.2295   0.02013   0.01306   0.0333   1.0000   0.9571
   0.500  -0.1780   0.01987   0.01273   0.0282   1.0000   0.9660
   0.750  -0.1276   0.01960   0.01243   0.0232   1.0000   0.9722
   1.000  -0.0894   0.01934   0.01216   0.0203   1.0000   0.9780
   1.250  -0.0540   0.01912   0.01195   0.0180   1.0000   0.9835
   1.500  -0.0174   0.01893   0.01180   0.0153   1.0000   0.9879
   1.750   0.0163   0.01880   0.01171   0.0132   1.0000   0.9924
   2.000   0.0493   0.01870   0.01168   0.0112   1.0000   0.9964
   2.250   0.0771   0.01866   0.01172   0.0102   1.0000   1.0000
   2.500   0.0841   0.01860   0.01174   0.0130   1.0000   1.0000
   2.750   0.0903   0.01857   0.01180   0.0158   1.0000   1.0000
   3.000   0.0957   0.01857   0.01189   0.0187   1.0000   1.0000
   3.250   0.1268   0.01876   0.01222   0.0168   0.9951   1.0000
   3.500   0.2499   0.01882   0.01262  -0.0012   0.9663   1.0000
   3.750   0.3769   0.01725   0.01153  -0.0179   0.9156   1.0000
   4.000   0.5185   0.01795   0.00926  -0.0347   0.2663   1.0000
   4.250   0.5362   0.01868   0.00971  -0.0331   0.2192   1.0000
   4.500   0.5536   0.01937   0.01018  -0.0315   0.1823   1.0000
   4.750   0.5703   0.02021   0.01080  -0.0297   0.1426   1.0000
   5.000   0.5874   0.02131   0.01172  -0.0278   0.1065   1.0000
   5.250   0.6059   0.02253   0.01271  -0.0263   0.0874   1.0000
   5.500   0.6263   0.02354   0.01373  -0.0249   0.0768   1.0000
   5.750   0.6470   0.02462   0.01493  -0.0234   0.0694   1.0000
   6.000   0.6668   0.02581   0.01611  -0.0221   0.0642   1.0000
   6.250   0.6874   0.02719   0.01774  -0.0205   0.0610   1.0000
   6.500   0.7068   0.02864   0.01931  -0.0190   0.0589   1.0000
   6.750   0.7250   0.03043   0.02120  -0.0174   0.0576   1.0000
   7.000   0.7407   0.03272   0.02374  -0.0153   0.0570   1.0000
   7.250   0.7518   0.03484   0.02625  -0.0122   0.0567   1.0000
   7.500   0.7589   0.03700   0.02885  -0.0087   0.0564   1.0000
   7.750   0.7628   0.03925   0.03151  -0.0047   0.0561   1.0000
   8.000   0.7637   0.04161   0.03424  -0.0005   0.0560   1.0000
   8.250   0.7627   0.04409   0.03703   0.0037   0.0561   1.0000
   8.500   0.7634   0.04671   0.03986   0.0074   0.0565   1.0000
   8.750   0.7389   0.05303   0.04716   0.0137   0.0634   1.0000
   9.000   0.7557   0.05663   0.05071   0.0140   0.0663   1.0000
   9.250   0.6577   0.07926   0.07493   0.0098   0.1346   1.0000
   9.500   0.6802   0.08255   0.07817   0.0106   0.1315   1.0000
   9.750   0.7126   0.08904   0.08449   0.0109   0.1294   1.0000
  10.000   0.6328   0.09641   0.09211  -0.0050   0.1251   1.0000
  10.250   0.6306   0.10145   0.09713  -0.0096   0.1207   1.0000
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