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NACA 2418 (naca2418-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 2418 (naca2418-il)
Reynolds number: 50,000
Max Cl/Cd: 8.55 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2418-il-50000.txt
Download as CSV file: xf-naca2418-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2418                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3154   0.11237   0.10410  -0.0195   1.0000   0.4102
  -9.250  -0.5654   0.07956   0.07157  -0.0393   1.0000   0.2507
  -9.000  -0.6067   0.07477   0.06686  -0.0360   1.0000   0.2494
  -8.750  -0.6563   0.06953   0.06165  -0.0321   1.0000   0.2480
  -8.500  -0.7067   0.06417   0.05621  -0.0277   1.0000   0.2470
  -8.250  -0.7485   0.05916   0.05099  -0.0233   1.0000   0.2475
  -8.000  -0.7806   0.05452   0.04597  -0.0192   1.0000   0.2498
  -7.750  -0.7682   0.05324   0.04479  -0.0171   1.0000   0.2557
  -7.500  -0.7649   0.05145   0.04293  -0.0146   1.0000   0.2618
  -7.250  -0.7755   0.04810   0.03914  -0.0118   1.0000   0.2678
  -7.000  -0.7648   0.04660   0.03765  -0.0099   1.0000   0.2745
  -6.750  -0.7550   0.04522   0.03618  -0.0079   1.0000   0.2827
  -6.500  -0.7501   0.04297   0.03360  -0.0061   1.0000   0.2910
  -6.250  -0.7338   0.04225   0.03299  -0.0046   1.0000   0.2999
  -6.000  -0.7242   0.04044   0.03085  -0.0032   1.0000   0.3102
  -5.750  -0.7073   0.03977   0.03029  -0.0018   1.0000   0.3203
  -5.500  -0.6935   0.03850   0.02885  -0.0006   1.0000   0.3319
  -5.250  -0.6776   0.03768   0.02798   0.0006   1.0000   0.3444
  -5.000  -0.6612   0.03697   0.02731   0.0018   1.0000   0.3570
  -4.750  -0.6452   0.03611   0.02634   0.0027   1.0000   0.3717
  -4.500  -0.6287   0.03545   0.02557   0.0036   1.0000   0.3884
  -4.250  -0.6117   0.03511   0.02540   0.0049   1.0000   0.4038
  -4.000  -0.5949   0.03473   0.02509   0.0059   1.0000   0.4208
  -3.750  -0.5782   0.03442   0.02484   0.0070   1.0000   0.4395
  -3.500  -0.5615   0.03419   0.02466   0.0080   1.0000   0.4589
  -3.250  -0.5448   0.03406   0.02460   0.0090   1.0000   0.4795
  -3.000  -0.5163   0.03422   0.02483   0.0079   0.9957   0.5051
  -2.750  -0.4705   0.03475   0.02545   0.0040   0.9835   0.5374
  -2.500  -0.4298   0.03525   0.02605   0.0013   0.9712   0.5699
  -2.250  -0.3924   0.03568   0.02662  -0.0007   0.9587   0.6024
  -2.000  -0.3562   0.03609   0.02708  -0.0025   0.9467   0.6390
  -1.750  -0.3175   0.03671   0.02789  -0.0038   0.9352   0.6754
  -1.500  -0.2942   0.03698   0.02828  -0.0027   0.9223   0.7103
  -1.250  -0.2684   0.03744   0.02885  -0.0018   0.9106   0.7498
  -1.000  -0.2312   0.03820   0.02972  -0.0019   0.8998   0.7944
  -0.750  -0.2124   0.03871   0.03030   0.0006   0.8872   0.8353
  -0.500  -0.1617   0.03989   0.03147  -0.0021   0.8758   0.8811
  -0.250  -0.0568   0.04161   0.03305  -0.0149   0.8633   0.9236
   0.000   0.0628   0.04302   0.03431  -0.0322   0.8493   0.9552
   0.250   0.2010   0.04348   0.03462  -0.0530   0.8369   0.9846
   0.500   0.2907   0.04310   0.03416  -0.0660   0.8249   1.0000
   0.750   0.2716   0.04344   0.03443  -0.0611   0.8106   1.0000
   1.000   0.2894   0.04332   0.03422  -0.0612   0.7999   1.0000
   1.250   0.2746   0.04368   0.03451  -0.0565   0.7867   1.0000
   1.500   0.2572   0.04422   0.03498  -0.0512   0.7742   1.0000
   1.750   0.2915   0.04422   0.03489  -0.0526   0.7642   1.0000
   2.000   0.2615   0.04528   0.03585  -0.0455   0.7507   1.0000
   2.250   0.2947   0.04556   0.03604  -0.0465   0.7404   1.0000
   2.500   0.2893   0.04654   0.03694  -0.0426   0.7275   1.0000
   2.750   0.2966   0.04749   0.03780  -0.0404   0.7154   1.0000
   3.000   0.3356   0.04769   0.03795  -0.0417   0.7044   1.0000
   3.250   0.3254   0.04928   0.03948  -0.0377   0.6908   1.0000
   3.500   0.3746   0.04922   0.03938  -0.0398   0.6807   1.0000
   3.750   0.3687   0.05089   0.04099  -0.0366   0.6669   1.0000
   4.000   0.3784   0.05224   0.04231  -0.0350   0.6546   1.0000
   4.250   0.4202   0.05230   0.04235  -0.0360   0.6439   1.0000
   4.500   0.4091   0.05465   0.04467  -0.0330   0.6302   1.0000
   4.750   0.4556   0.05451   0.04453  -0.0342   0.6204   1.0000
   5.000   0.4493   0.05684   0.04684  -0.0318   0.6068   1.0000
   5.250   0.4548   0.05880   0.04879  -0.0303   0.5946   1.0000
   5.500   0.4972   0.05869   0.04870  -0.0308   0.5842   1.0000
   5.750   0.4786   0.06219   0.05218  -0.0284   0.5709   1.0000
   6.000   0.5275   0.06167   0.05168  -0.0290   0.5611   1.0000
   6.250   0.5078   0.06549   0.05550  -0.0270   0.5481   1.0000
   6.500   0.5179   0.06752   0.05754  -0.0261   0.5368   1.0000
   6.750   0.5421   0.06855   0.05860  -0.0257   0.5258   1.0000
   7.000   0.5288   0.07237   0.06242  -0.0245   0.5145   1.0000
   7.250   0.5850   0.07096   0.06105  -0.0244   0.5037   1.0000
   7.500   0.5428   0.07720   0.06728  -0.0232   0.4928   1.0000
   7.750   0.5920   0.07628   0.06641  -0.0227   0.4813   1.0000
   8.000   0.5585   0.08204   0.07217  -0.0221   0.4713   1.0000
   8.250   0.5861   0.08287   0.07303  -0.0214   0.4598   1.0000
   8.500   0.5758   0.08689   0.07708  -0.0212   0.4500   1.0000
   8.750   0.5889   0.08901   0.07923  -0.0206   0.4391   1.0000
   9.000   0.5926   0.09197   0.08224  -0.0204   0.4292   1.0000
   9.250   0.5944   0.09524   0.08553  -0.0202   0.4195   1.0000
   9.500   0.5996   0.09823   0.08856  -0.0201   0.4102   1.0000
   9.750   0.6016   0.10165   0.09200  -0.0201   0.4012   1.0000
  10.000   0.5897   0.10648   0.09687  -0.0208   0.3953   1.0000
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