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NACA 2408 (naca2408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.81 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2408-il-1000000.txt
Download as CSV file: xf-naca2408-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.8523   0.03757   0.03547  -0.0512   1.0000   0.0059
 -10.500  -0.8601   0.03067   0.02806  -0.0529   1.0000   0.0060
 -10.250  -0.8550   0.02660   0.02360  -0.0526   1.0000   0.0062
 -10.000  -0.8389   0.02485   0.02170  -0.0520   1.0000   0.0064
  -9.750  -0.8199   0.02379   0.02054  -0.0513   1.0000   0.0067
  -9.500  -0.8012   0.02264   0.01925  -0.0505   1.0000   0.0069
  -9.250  -0.7832   0.02130   0.01774  -0.0495   1.0000   0.0072
  -9.000  -0.7655   0.01988   0.01613  -0.0483   1.0000   0.0074
  -8.750  -0.7471   0.01859   0.01465  -0.0471   1.0000   0.0077
  -8.500  -0.7280   0.01749   0.01337  -0.0458   1.0000   0.0079
  -8.250  -0.7080   0.01660   0.01231  -0.0446   1.0000   0.0081
  -8.000  -0.6871   0.01595   0.01154  -0.0435   1.0000   0.0083
  -7.750  -0.6705   0.01379   0.00905  -0.0420   1.0000   0.0090
  -7.500  -0.6492   0.01309   0.00828  -0.0409   1.0000   0.0095
  -7.250  -0.6271   0.01262   0.00775  -0.0400   1.0000   0.0101
  -7.000  -0.5952   0.01217   0.00723  -0.0411   0.9990   0.0108
  -6.750  -0.5616   0.01178   0.00679  -0.0425   0.9977   0.0116
  -6.500  -0.5285   0.01080   0.00564  -0.0438   0.9963   0.0130
  -6.250  -0.4933   0.01035   0.00517  -0.0456   0.9950   0.0149
  -6.000  -0.4591   0.01008   0.00488  -0.0470   0.9931   0.0166
  -5.750  -0.4258   0.00958   0.00433  -0.0483   0.9909   0.0196
  -5.500  -0.3914   0.00944   0.00424  -0.0498   0.9891   0.0233
  -5.250  -0.3562   0.00942   0.00421  -0.0514   0.9876   0.0254
  -5.000  -0.3216   0.00891   0.00366  -0.0530   0.9864   0.0296
  -4.750  -0.2881   0.00874   0.00351  -0.0543   0.9841   0.0327
  -4.500  -0.2559   0.00859   0.00332  -0.0552   0.9808   0.0346
  -4.250  -0.2227   0.00847   0.00320  -0.0564   0.9779   0.0356
  -4.000  -0.1916   0.00800   0.00266  -0.0571   0.9741   0.0382
  -3.750  -0.1628   0.00774   0.00238  -0.0572   0.9680   0.0406
  -3.500  -0.1331   0.00752   0.00214  -0.0575   0.9628   0.0429
  -3.250  -0.1060   0.00734   0.00194  -0.0572   0.9547   0.0449
  -3.000  -0.0784   0.00715   0.00171  -0.0570   0.9469   0.0498
  -2.750  -0.0517   0.00686   0.00151  -0.0566   0.9380   0.0720
  -2.500  -0.0252   0.00658   0.00137  -0.0563   0.9278   0.1135
  -2.250   0.0015   0.00635   0.00125  -0.0560   0.9175   0.1515
  -2.000   0.0283   0.00615   0.00115  -0.0557   0.9063   0.1909
  -1.750   0.0551   0.00597   0.00106  -0.0555   0.8938   0.2335
  -1.500   0.0819   0.00579   0.00099  -0.0552   0.8803   0.2814
  -1.250   0.1087   0.00560   0.00093  -0.0550   0.8661   0.3386
  -1.000   0.1353   0.00534   0.00088  -0.0548   0.8511   0.4206
  -0.750   0.1615   0.00502   0.00085  -0.0545   0.8347   0.5331
  -0.500   0.1875   0.00475   0.00084  -0.0541   0.8171   0.6366
  -0.250   0.2123   0.00444   0.00085  -0.0534   0.7982   0.7563
   0.000   0.2341   0.00419   0.00088  -0.0517   0.7707   0.8732
   0.250   0.2592   0.00417   0.00090  -0.0505   0.7361   0.9644
   0.500   0.2995   0.00430   0.00090  -0.0532   0.7022   0.9932
   0.750   0.3336   0.00448   0.00090  -0.0546   0.6632   1.0000
   1.000   0.3593   0.00464   0.00092  -0.0541   0.6308   1.0000
   1.250   0.3851   0.00481   0.00095  -0.0537   0.5973   1.0000
   1.500   0.4108   0.00501   0.00099  -0.0532   0.5619   1.0000
   1.750   0.4368   0.00521   0.00105  -0.0529   0.5279   1.0000
   2.000   0.4629   0.00541   0.00112  -0.0525   0.4945   1.0000
   2.250   0.4888   0.00566   0.00119  -0.0522   0.4544   1.0000
   2.500   0.5148   0.00593   0.00129  -0.0518   0.4117   1.0000
   2.750   0.5404   0.00625   0.00141  -0.0515   0.3624   1.0000
   3.000   0.5646   0.00680   0.00160  -0.0510   0.2804   1.0000
   3.250   0.5883   0.00746   0.00187  -0.0505   0.1907   1.0000
   3.500   0.6121   0.00813   0.00218  -0.0499   0.1091   1.0000
   3.750   0.6370   0.00865   0.00246  -0.0495   0.0586   1.0000
   4.000   0.6631   0.00897   0.00268  -0.0492   0.0433   1.0000
   4.250   0.6898   0.00919   0.00290  -0.0490   0.0394   1.0000
   4.500   0.7165   0.00942   0.00315  -0.0488   0.0374   1.0000
   4.750   0.7431   0.00965   0.00341  -0.0485   0.0365   1.0000
   5.000   0.7695   0.00992   0.00372  -0.0483   0.0349   1.0000
   5.250   0.7956   0.01023   0.00406  -0.0480   0.0331   1.0000
   5.500   0.8213   0.01059   0.00445  -0.0476   0.0312   1.0000
   5.750   0.8465   0.01104   0.00494  -0.0472   0.0293   1.0000
   6.000   0.8697   0.01179   0.00581  -0.0464   0.0272   1.0000
   6.250   0.8961   0.01199   0.00603  -0.0462   0.0266   1.0000
   6.500   0.9227   0.01216   0.00621  -0.0461   0.0258   1.0000
   6.750   0.9491   0.01235   0.00641  -0.0459   0.0243   1.0000
   7.000   0.9752   0.01258   0.00666  -0.0457   0.0222   1.0000
   7.250   1.0008   0.01286   0.00693  -0.0454   0.0201   1.0000
   7.500   1.0235   0.01358   0.00772  -0.0447   0.0176   1.0000
   7.750   1.0508   0.01360   0.00773  -0.0446   0.0162   1.0000
   8.000   1.0773   0.01372   0.00781  -0.0445   0.0143   1.0000
   8.250   1.0995   0.01449   0.00860  -0.0437   0.0118   1.0000
   8.500   1.1243   0.01484   0.00898  -0.0433   0.0111   1.0000
   8.750   1.1483   0.01527   0.00947  -0.0428   0.0102   1.0000
   9.000   1.1718   0.01576   0.00997  -0.0422   0.0094   1.0000
   9.250   1.1912   0.01681   0.01111  -0.0410   0.0083   1.0000
   9.500   1.2107   0.01780   0.01222  -0.0398   0.0079   1.0000
   9.750   1.2331   0.01836   0.01286  -0.0391   0.0075   1.0000
  10.000   1.2545   0.01902   0.01359  -0.0383   0.0071   1.0000
  10.250   1.2753   0.01972   0.01436  -0.0374   0.0067   1.0000
  10.500   1.2952   0.02050   0.01520  -0.0364   0.0064   1.0000
  10.750   1.3133   0.02144   0.01625  -0.0353   0.0060   1.0000
  11.000   1.3251   0.02309   0.01807  -0.0332   0.0057   1.0000
  11.250   1.3301   0.02552   0.02077  -0.0304   0.0054   1.0000
  11.500   1.3452   0.02657   0.02194  -0.0289   0.0053   1.0000
  11.750   1.3576   0.02781   0.02332  -0.0272   0.0052   1.0000
  12.000   1.3658   0.02918   0.02485  -0.0248   0.0051   1.0000
  12.250   1.3699   0.03070   0.02651  -0.0221   0.0050   1.0000
  12.500   1.3719   0.03238   0.02836  -0.0194   0.0049   1.0000
  12.750   1.3714   0.03437   0.03051  -0.0170   0.0048   1.0000
  13.000   1.3699   0.03655   0.03285  -0.0150   0.0047   1.0000
  13.250   1.3655   0.03921   0.03568  -0.0135   0.0047   1.0000
  13.500   1.3592   0.04231   0.03896  -0.0126   0.0046   1.0000
  13.750   1.3513   0.04592   0.04275  -0.0126   0.0046   1.0000
  14.000   1.3399   0.05038   0.04740  -0.0134   0.0045   1.0000
  14.250   1.3277   0.05541   0.05261  -0.0152   0.0045   1.0000
  14.500   1.3111   0.06165   0.05903  -0.0182   0.0045   1.0000
  14.750   1.2908   0.06902   0.06658  -0.0222   0.0045   1.0000
  15.000   1.2658   0.07780   0.07554  -0.0273   0.0045   1.0000
  15.250   1.2337   0.08851   0.08643  -0.0335   0.0046   1.0000
  15.500   1.1937   0.10179   0.09991  -0.0411   0.0047   1.0000
  15.750   1.1480   0.11729   0.11558  -0.0495   0.0049   1.0000
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