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NACA 2408 (naca2408-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 200,000
Max Cl/Cd: 58.86 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2408-il-200000-n5.txt
Download as CSV file: xf-naca2408-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5597   0.08283   0.07932  -0.0182   1.0000   0.0149
  -8.750  -0.5671   0.07690   0.07345  -0.0223   1.0000   0.0148
  -8.500  -0.5762   0.06961   0.06622  -0.0293   1.0000   0.0147
  -8.250  -0.5855   0.05851   0.05507  -0.0397   1.0000   0.0145
  -8.000  -0.6101   0.04154   0.03752  -0.0473   1.0000   0.0142
  -7.750  -0.6123   0.03383   0.02910  -0.0477   1.0000   0.0146
  -7.500  -0.6017   0.02975   0.02447  -0.0468   1.0000   0.0155
  -7.250  -0.5866   0.02671   0.02087  -0.0458   1.0000   0.0167
  -7.000  -0.5696   0.02406   0.01775  -0.0446   1.0000   0.0176
  -6.750  -0.5506   0.02231   0.01575  -0.0437   1.0000   0.0186
  -6.500  -0.5297   0.02128   0.01456  -0.0428   1.0000   0.0198
  -6.250  -0.5082   0.02036   0.01345  -0.0418   1.0000   0.0217
  -6.000  -0.4861   0.01936   0.01219  -0.0409   1.0000   0.0241
  -5.750  -0.4637   0.01836   0.01095  -0.0399   1.0000   0.0258
  -5.500  -0.4419   0.01727   0.00981  -0.0391   1.0000   0.0284
  -5.250  -0.4191   0.01678   0.00923  -0.0384   1.0000   0.0318
  -5.000  -0.3958   0.01617   0.00843  -0.0375   1.0000   0.0347
  -4.750  -0.3724   0.01535   0.00758  -0.0370   0.9999   0.0382
  -4.500  -0.3368   0.01482   0.00698  -0.0389   0.9963   0.0426
  -4.250  -0.3011   0.01439   0.00641  -0.0407   0.9924   0.0464
  -4.000  -0.2660   0.01367   0.00567  -0.0425   0.9882   0.0507
  -3.750  -0.2304   0.01324   0.00519  -0.0443   0.9840   0.0557
  -3.500  -0.1958   0.01281   0.00470  -0.0458   0.9790   0.0609
  -3.250  -0.1595   0.01239   0.00427  -0.0477   0.9752   0.0701
  -3.000  -0.1266   0.01200   0.00392  -0.0488   0.9690   0.0868
  -2.750  -0.0909   0.01158   0.00363  -0.0507   0.9646   0.1190
  -2.500  -0.0597   0.01124   0.00340  -0.0515   0.9572   0.1587
  -2.250  -0.0255   0.01084   0.00322  -0.0530   0.9515   0.2144
  -2.000   0.0043   0.01045   0.00308  -0.0536   0.9426   0.2814
  -1.750   0.0365   0.00991   0.00293  -0.0547   0.9358   0.3866
  -1.500   0.0633   0.00927   0.00286  -0.0546   0.9255   0.5327
  -1.250   0.0889   0.00871   0.00283  -0.0538   0.9153   0.6785
  -1.000   0.1142   0.00831   0.00280  -0.0525   0.9051   0.7987
  -0.750   0.1493   0.00810   0.00277  -0.0530   0.8953   0.9166
  -0.500   0.1970   0.00801   0.00264  -0.0570   0.8850   0.9878
  -0.250   0.2306   0.00797   0.00251  -0.0580   0.8710   1.0000
   0.000   0.2579   0.00797   0.00242  -0.0577   0.8549   1.0000
   0.250   0.2849   0.00798   0.00234  -0.0573   0.8380   1.0000
   0.500   0.3114   0.00801   0.00229  -0.0568   0.8196   1.0000
   0.750   0.3377   0.00807   0.00225  -0.0562   0.8001   1.0000
   1.000   0.3639   0.00814   0.00224  -0.0556   0.7800   1.0000
   1.250   0.3899   0.00823   0.00224  -0.0550   0.7584   1.0000
   1.500   0.4159   0.00834   0.00226  -0.0544   0.7362   1.0000
   1.750   0.4415   0.00848   0.00230  -0.0538   0.7101   1.0000
   2.000   0.4664   0.00867   0.00233  -0.0529   0.6749   1.0000
   2.250   0.4907   0.00892   0.00237  -0.0520   0.6333   1.0000
   2.500   0.5153   0.00917   0.00247  -0.0512   0.5941   1.0000
   2.750   0.5400   0.00945   0.00258  -0.0504   0.5585   1.0000
   3.000   0.5643   0.00977   0.00272  -0.0497   0.5164   1.0000
   3.250   0.5886   0.01011   0.00290  -0.0490   0.4731   1.0000
   3.500   0.6133   0.01044   0.00309  -0.0484   0.4330   1.0000
   3.750   0.6375   0.01083   0.00331  -0.0477   0.3865   1.0000
   4.000   0.6617   0.01125   0.00358  -0.0471   0.3394   1.0000
   4.250   0.6840   0.01194   0.00392  -0.0464   0.2626   1.0000
   4.500   0.7049   0.01291   0.00440  -0.0455   0.1688   1.0000
   4.750   0.7269   0.01375   0.00493  -0.0449   0.1042   1.0000
   5.000   0.7501   0.01445   0.00548  -0.0442   0.0700   1.0000
   5.250   0.7742   0.01501   0.00601  -0.0436   0.0549   1.0000
   5.500   0.7982   0.01559   0.00657  -0.0430   0.0486   1.0000
   5.750   0.8224   0.01611   0.00719  -0.0424   0.0458   1.0000
   6.000   0.8461   0.01669   0.00788  -0.0418   0.0426   1.0000
   6.250   0.8685   0.01744   0.00867  -0.0410   0.0394   1.0000
   6.500   0.8899   0.01833   0.00963  -0.0400   0.0371   1.0000
   6.750   0.9127   0.01900   0.01042  -0.0393   0.0348   1.0000
   7.000   0.9346   0.01981   0.01134  -0.0384   0.0325   1.0000
   7.250   0.9557   0.02071   0.01230  -0.0375   0.0298   1.0000
   7.500   0.9726   0.02244   0.01408  -0.0361   0.0269   1.0000
   7.750   0.9953   0.02316   0.01498  -0.0353   0.0254   1.0000
   8.000   1.0170   0.02404   0.01602  -0.0344   0.0229   1.0000
   8.250   1.0377   0.02506   0.01716  -0.0335   0.0208   1.0000
   8.500   1.0573   0.02623   0.01840  -0.0325   0.0193   1.0000
   8.750   1.0738   0.02825   0.02050  -0.0313   0.0178   1.0000
   9.000   1.0940   0.02928   0.02179  -0.0302   0.0165   1.0000
   9.250   1.1123   0.03074   0.02354  -0.0290   0.0151   1.0000
   9.500   1.1286   0.03247   0.02551  -0.0276   0.0142   1.0000
   9.750   1.1435   0.03414   0.02740  -0.0262   0.0135   1.0000
  10.000   1.1570   0.03576   0.02920  -0.0248   0.0129   1.0000
  10.250   1.1684   0.03737   0.03096  -0.0233   0.0124   1.0000
  10.500   1.1721   0.04014   0.03397  -0.0212   0.0118   1.0000
  10.750   1.1749   0.04271   0.03692  -0.0188   0.0114   1.0000
  11.000   1.1702   0.04552   0.04009  -0.0158   0.0110   1.0000
  11.250   1.1610   0.04870   0.04359  -0.0132   0.0107   1.0000
  11.500   1.1478   0.05237   0.04756  -0.0113   0.0105   1.0000
  11.750   1.1315   0.05670   0.05217  -0.0106   0.0104   1.0000
  12.000   1.1128   0.06183   0.05756  -0.0115   0.0103   1.0000
  12.250   1.0922   0.06794   0.06393  -0.0140   0.0103   1.0000
  12.500   1.0699   0.07529   0.07149  -0.0183   0.0104   1.0000
  12.750   1.0458   0.08410   0.08050  -0.0243   0.0105   1.0000
  13.000   1.0195   0.09465   0.09121  -0.0317   0.0108   1.0000
  13.250   0.9916   0.10681   0.10347  -0.0397   0.0112   1.0000
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