Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 2408 (naca2408-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 500,000
Max Cl/Cd: 80.56 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2408-il-500000.txt
Download as CSV file: xf-naca2408-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2408                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5372   0.10797   0.10566  -0.0038   1.0000   0.0208
  -9.750  -0.5347   0.10401   0.10171  -0.0057   1.0000   0.0215
  -8.250  -0.6631   0.02974   0.02622  -0.0489   1.0000   0.0126
  -8.000  -0.6535   0.02627   0.02235  -0.0476   1.0000   0.0129
  -7.750  -0.6375   0.02446   0.02032  -0.0465   1.0000   0.0134
  -7.500  -0.6185   0.02359   0.01931  -0.0454   1.0000   0.0141
  -7.250  -0.6000   0.02233   0.01787  -0.0441   1.0000   0.0149
  -7.000  -0.5822   0.02049   0.01573  -0.0428   1.0000   0.0157
  -6.750  -0.5631   0.01883   0.01379  -0.0414   1.0000   0.0165
  -6.500  -0.5422   0.01782   0.01255  -0.0402   1.0000   0.0171
  -6.250  -0.5228   0.01515   0.00951  -0.0391   1.0000   0.0187
  -6.000  -0.5005   0.01481   0.00915  -0.0382   1.0000   0.0204
  -5.750  -0.4779   0.01448   0.00876  -0.0374   1.0000   0.0225
  -5.500  -0.4548   0.01399   0.00817  -0.0365   1.0000   0.0245
  -5.250  -0.4271   0.01293   0.00696  -0.0367   0.9994   0.0273
  -5.000  -0.3903   0.01254   0.00656  -0.0388   0.9971   0.0316
  -4.750  -0.3529   0.01234   0.00628  -0.0409   0.9951   0.0351
  -4.500  -0.3189   0.01137   0.00527  -0.0425   0.9927   0.0404
  -4.250  -0.2830   0.01106   0.00491  -0.0443   0.9898   0.0444
  -4.000  -0.2458   0.01083   0.00463  -0.0463   0.9874   0.0468
  -3.750  -0.2095   0.01012   0.00388  -0.0483   0.9854   0.0510
  -3.500  -0.1754   0.00979   0.00353  -0.0497   0.9812   0.0547
  -3.250  -0.1385   0.00948   0.00318  -0.0516   0.9783   0.0587
  -3.000  -0.1004   0.00905   0.00279  -0.0539   0.9763   0.0717
  -2.750  -0.0671   0.00851   0.00249  -0.0552   0.9716   0.1258
  -2.500  -0.0329   0.00810   0.00231  -0.0567   0.9672   0.1868
  -2.250   0.0008   0.00774   0.00215  -0.0580   0.9627   0.2466
  -2.000   0.0301   0.00740   0.00202  -0.0583   0.9548   0.3087
  -1.750   0.0596   0.00702   0.00189  -0.0587   0.9476   0.3871
  -1.500   0.0865   0.00652   0.00179  -0.0586   0.9384   0.5061
  -1.250   0.1110   0.00599   0.00174  -0.0577   0.9276   0.6506
  -1.000   0.1333   0.00550   0.00172  -0.0561   0.9164   0.7878
  -0.750   0.1543   0.00518   0.00175  -0.0536   0.9046   0.9214
  -0.500   0.1985   0.00514   0.00169  -0.0567   0.8947   0.9839
  -0.250   0.2396   0.00512   0.00160  -0.0594   0.8818   1.0000
   0.000   0.2651   0.00513   0.00153  -0.0587   0.8654   1.0000
   0.250   0.2906   0.00517   0.00147  -0.0581   0.8472   1.0000
   0.500   0.3159   0.00522   0.00142  -0.0573   0.8247   1.0000
   0.750   0.3407   0.00532   0.00137  -0.0564   0.7950   1.0000
   1.000   0.3658   0.00544   0.00135  -0.0556   0.7642   1.0000
   1.250   0.3911   0.00558   0.00135  -0.0549   0.7336   1.0000
   1.500   0.4164   0.00574   0.00136  -0.0542   0.7004   1.0000
   1.750   0.4417   0.00593   0.00140  -0.0536   0.6663   1.0000
   2.000   0.4670   0.00613   0.00145  -0.0530   0.6315   1.0000
   2.250   0.4925   0.00635   0.00152  -0.0524   0.5963   1.0000
   2.500   0.5179   0.00659   0.00162  -0.0519   0.5612   1.0000
   2.750   0.5437   0.00681   0.00172  -0.0515   0.5298   1.0000
   3.000   0.5694   0.00707   0.00184  -0.0511   0.4936   1.0000
   3.250   0.5945   0.00738   0.00198  -0.0506   0.4480   1.0000
   3.500   0.6197   0.00772   0.00214  -0.0501   0.4019   1.0000
   3.750   0.6441   0.00820   0.00235  -0.0496   0.3373   1.0000
   4.000   0.6673   0.00887   0.00265  -0.0490   0.2524   1.0000
   4.250   0.6893   0.00976   0.00307  -0.0483   0.1540   1.0000
   4.500   0.7117   0.01063   0.00356  -0.0476   0.0766   1.0000
   4.750   0.7367   0.01112   0.00393  -0.0471   0.0546   1.0000
   5.000   0.7622   0.01153   0.00434  -0.0467   0.0483   1.0000
   5.250   0.7877   0.01190   0.00476  -0.0463   0.0453   1.0000
   5.500   0.8128   0.01236   0.00525  -0.0458   0.0425   1.0000
   5.750   0.8367   0.01297   0.00590  -0.0451   0.0393   1.0000
   6.000   0.8597   0.01371   0.00674  -0.0443   0.0373   1.0000
   6.250   0.8845   0.01414   0.00723  -0.0438   0.0359   1.0000
   6.500   0.9085   0.01469   0.00785  -0.0432   0.0339   1.0000
   6.750   0.9319   0.01531   0.00851  -0.0426   0.0311   1.0000
   7.000   0.9485   0.01711   0.01040  -0.0409   0.0272   1.0000
   7.250   0.9735   0.01745   0.01083  -0.0404   0.0258   1.0000
   7.500   0.9981   0.01786   0.01131  -0.0399   0.0233   1.0000
   7.750   1.0218   0.01835   0.01184  -0.0394   0.0208   1.0000
   8.000   1.0417   0.01952   0.01304  -0.0383   0.0188   1.0000
   8.250   1.0600   0.02130   0.01497  -0.0369   0.0173   1.0000
   8.500   1.0833   0.02183   0.01560  -0.0362   0.0161   1.0000
   8.750   1.1059   0.02239   0.01625  -0.0355   0.0147   1.0000
   9.000   1.1280   0.02290   0.01684  -0.0349   0.0137   1.0000
   9.250   1.1484   0.02371   0.01771  -0.0340   0.0129   1.0000
   9.500   1.1572   0.02754   0.02187  -0.0316   0.0119   1.0000
   9.750   1.1737   0.02917   0.02371  -0.0302   0.0115   1.0000
  10.000   1.1882   0.03107   0.02587  -0.0285   0.0112   1.0000
  10.250   1.1995   0.03333   0.02839  -0.0266   0.0108   1.0000
  10.500   1.2088   0.03551   0.03083  -0.0246   0.0103   1.0000
  10.750   1.2172   0.03738   0.03290  -0.0227   0.0099   1.0000
  11.000   1.2243   0.03902   0.03470  -0.0207   0.0095   1.0000
  11.250   1.2247   0.04088   0.03675  -0.0180   0.0093   1.0000
  11.500   1.2177   0.04344   0.03952  -0.0149   0.0091   1.0000
  11.750   1.2072   0.04645   0.04275  -0.0125   0.0090   1.0000
  12.000   1.1929   0.05015   0.04668  -0.0110   0.0090   1.0000
  12.250   1.1711   0.05534   0.05213  -0.0108   0.0090   1.0000
  12.500   1.1430   0.06224   0.05931  -0.0128   0.0091   1.0000
  12.750   1.0839   0.07634   0.07384  -0.0207   0.0095   1.0000
  13.000   1.0398   0.09048   0.08823  -0.0307   0.0099   1.0000
<< Back to NACA 2408 (naca2408-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2408 (naca2408-il)