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NACA 2408 (naca2408-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 50,000
Max Cl/Cd: 36.67 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2408-il-50000-n5.txt
Download as CSV file: xf-naca2408-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5217   0.09473   0.08766  -0.0178   1.0000   0.0540
  -8.500  -0.5231   0.09027   0.08328  -0.0204   1.0000   0.0537
  -8.250  -0.5256   0.08569   0.07878  -0.0234   1.0000   0.0537
  -8.000  -0.5262   0.08051   0.07364  -0.0278   1.0000   0.0537
  -7.750  -0.5256   0.07499   0.06813  -0.0321   1.0000   0.0538
  -7.500  -0.5240   0.06940   0.06249  -0.0359   1.0000   0.0540
  -7.250  -0.5214   0.06382   0.05679  -0.0391   1.0000   0.0543
  -7.000  -0.5171   0.05833   0.05109  -0.0415   1.0000   0.0546
  -6.750  -0.5105   0.05301   0.04545  -0.0431   1.0000   0.0548
  -6.500  -0.5007   0.04803   0.04006  -0.0440   1.0000   0.0554
  -6.250  -0.4881   0.04336   0.03481  -0.0444   1.0000   0.0573
  -6.000  -0.4728   0.03947   0.03035  -0.0442   1.0000   0.0604
  -5.750  -0.4546   0.03713   0.02784  -0.0436   1.0000   0.0637
  -5.500  -0.4347   0.03427   0.02448  -0.0430   1.0000   0.0666
  -5.250  -0.4127   0.03177   0.02120  -0.0423   1.0000   0.0729
  -5.000  -0.3916   0.02988   0.01928  -0.0416   1.0000   0.0775
  -4.750  -0.3684   0.02801   0.01706  -0.0408   1.0000   0.0822
  -4.500  -0.3456   0.02661   0.01544  -0.0400   1.0000   0.0904
  -4.250  -0.3220   0.02528   0.01385  -0.0391   1.0000   0.0972
  -4.000  -0.2979   0.02396   0.01235  -0.0382   1.0000   0.1032
  -3.750  -0.2740   0.02290   0.01118  -0.0373   1.0000   0.1117
  -3.500  -0.2500   0.02200   0.01022  -0.0367   1.0000   0.1258
  -3.250  -0.2261   0.02117   0.00942  -0.0361   1.0000   0.1483
  -3.000  -0.2019   0.02027   0.00859  -0.0356   1.0000   0.1798
  -2.750  -0.1780   0.01941   0.00802  -0.0353   1.0000   0.2405
  -2.500  -0.1549   0.01847   0.00761  -0.0350   1.0000   0.3467
  -2.250  -0.1348   0.01736   0.00736  -0.0336   1.0000   0.5143
  -2.000  -0.1199   0.01639   0.00733  -0.0294   1.0000   0.7577
  -1.750  -0.0793   0.01607   0.00695  -0.0313   1.0000   1.0000
  -1.500  -0.0579   0.01616   0.00673  -0.0306   1.0000   1.0000
  -1.250  -0.0363   0.01628   0.00657  -0.0300   1.0000   1.0000
  -1.000  -0.0147   0.01644   0.00651  -0.0294   1.0000   1.0000
  -0.750   0.0068   0.01664   0.00651  -0.0288   1.0000   1.0000
  -0.500   0.0283   0.01687   0.00656  -0.0284   1.0000   1.0000
  -0.250   0.0604   0.01717   0.00670  -0.0300   0.9950   1.0000
   0.000   0.1037   0.01747   0.00686  -0.0337   0.9828   1.0000
   0.250   0.1460   0.01775   0.00702  -0.0372   0.9700   1.0000
   0.500   0.1874   0.01801   0.00720  -0.0403   0.9566   1.0000
   0.750   0.2282   0.01823   0.00739  -0.0432   0.9428   1.0000
   1.000   0.2688   0.01842   0.00757  -0.0460   0.9287   1.0000
   1.250   0.3092   0.01859   0.00775  -0.0486   0.9144   1.0000
   1.500   0.3476   0.01872   0.00793  -0.0507   0.8993   1.0000
   1.750   0.3845   0.01882   0.00809  -0.0523   0.8835   1.0000
   2.000   0.4203   0.01889   0.00825  -0.0536   0.8673   1.0000
   2.250   0.4552   0.01895   0.00839  -0.0546   0.8508   1.0000
   2.500   0.4851   0.01906   0.00860  -0.0546   0.8310   1.0000
   2.750   0.5165   0.01912   0.00879  -0.0547   0.8120   1.0000
   3.000   0.5476   0.01917   0.00894  -0.0547   0.7928   1.0000
   3.250   0.5751   0.01930   0.00919  -0.0540   0.7705   1.0000
   3.500   0.6044   0.01935   0.00937  -0.0534   0.7493   1.0000
   3.750   0.6305   0.01951   0.00965  -0.0524   0.7245   1.0000
   4.000   0.6568   0.01965   0.00991  -0.0513   0.6986   1.0000
   4.250   0.6825   0.01980   0.01019  -0.0499   0.6703   1.0000
   4.500   0.7067   0.01990   0.01032  -0.0481   0.6342   1.0000
   4.750   0.7271   0.02003   0.01038  -0.0454   0.5814   1.0000
   5.000   0.7452   0.02032   0.01042  -0.0425   0.5128   1.0000
   5.250   0.7624   0.02087   0.01073  -0.0400   0.4340   1.0000
   5.500   0.7793   0.02170   0.01121  -0.0379   0.3431   1.0000
   5.750   0.7948   0.02305   0.01204  -0.0361   0.2373   1.0000
   6.000   0.8091   0.02506   0.01345  -0.0346   0.1519   1.0000
   6.250   0.8255   0.02696   0.01508  -0.0333   0.1170   1.0000
   6.500   0.8433   0.02857   0.01664  -0.0320   0.0987   1.0000
   6.750   0.8620   0.03009   0.01823  -0.0307   0.0888   1.0000
   7.000   0.8825   0.03166   0.01998  -0.0294   0.0826   1.0000
   7.250   0.9045   0.03333   0.02180  -0.0282   0.0773   1.0000
   7.500   0.9267   0.03518   0.02374  -0.0273   0.0711   1.0000
   7.750   0.9492   0.03700   0.02583  -0.0264   0.0649   1.0000
   8.000   0.9721   0.03935   0.02828  -0.0257   0.0613   1.0000
   8.250   0.9925   0.04184   0.03124  -0.0245   0.0568   1.0000
   8.500   1.0105   0.04440   0.03416  -0.0234   0.0529   1.0000
   8.750   1.0271   0.04733   0.03736  -0.0223   0.0507   1.0000
   9.000   1.0398   0.05072   0.04097  -0.0211   0.0484   1.0000
   9.250   1.0445   0.05434   0.04526  -0.0191   0.0464   1.0000
   9.500   1.0455   0.05820   0.04964  -0.0173   0.0449   1.0000
   9.750   1.0420   0.06233   0.05421  -0.0155   0.0442   1.0000
  10.000   1.0333   0.06659   0.05883  -0.0138   0.0439   1.0000
  10.250   1.0188   0.07078   0.06332  -0.0123   0.0438   1.0000
  10.500   0.9999   0.07518   0.06794  -0.0115   0.0439   1.0000
  10.750   0.9786   0.08028   0.07324  -0.0124   0.0442   1.0000
  11.000   0.9560   0.08640   0.07951  -0.0152   0.0446   1.0000
  11.250   0.9334   0.09376   0.08697  -0.0200   0.0451   1.0000
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