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NACA 2410 (naca2410-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 2410 (naca2410-il)
Reynolds number: 200,000
Max Cl/Cd: 67.27 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2410-il-200000.txt
Download as CSV file: xf-naca2410-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2410                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3936   0.11300   0.10942  -0.0212   1.0000   0.0626
 -11.000  -0.3908   0.10977   0.10620  -0.0218   1.0000   0.0651
 -10.750  -0.5323   0.11221   0.10849  -0.0161   1.0000   0.0601
 -10.500  -0.5207   0.10975   0.10602  -0.0149   1.0000   0.0616
 -10.250  -0.5144   0.10664   0.10291  -0.0154   1.0000   0.0635
 -10.000  -0.4153   0.09108   0.08760  -0.0291   1.0000   0.0730
  -9.750  -0.4053   0.08850   0.08503  -0.0280   1.0000   0.0750
  -9.500  -0.4044   0.08480   0.08134  -0.0286   1.0000   0.0772
  -9.250  -0.4099   0.08027   0.07683  -0.0302   1.0000   0.0798
  -9.000  -0.6155   0.05953   0.05580  -0.0500   1.0000   0.0466
  -8.750  -0.6276   0.05395   0.05008  -0.0505   1.0000   0.0457
  -8.500  -0.6408   0.04803   0.04387  -0.0499   1.0000   0.0450
  -8.250  -0.6495   0.04243   0.03787  -0.0484   1.0000   0.0450
  -8.000  -0.6516   0.03762   0.03256  -0.0463   1.0000   0.0454
  -7.750  -0.6474   0.03363   0.02804  -0.0441   1.0000   0.0461
  -7.500  -0.6367   0.03108   0.02496  -0.0419   1.0000   0.0473
  -7.250  -0.6259   0.02760   0.02116  -0.0404   1.0000   0.0495
  -7.000  -0.6080   0.02652   0.02005  -0.0391   1.0000   0.0518
  -6.750  -0.5898   0.02503   0.01832  -0.0377   1.0000   0.0541
  -6.500  -0.5707   0.02382   0.01679  -0.0362   1.0000   0.0569
  -6.250  -0.5509   0.02243   0.01507  -0.0349   1.0000   0.0593
  -6.000  -0.5302   0.02077   0.01335  -0.0341   1.0000   0.0620
  -5.750  -0.5089   0.02010   0.01261  -0.0331   1.0000   0.0653
  -5.500  -0.4867   0.01934   0.01169  -0.0321   1.0000   0.0682
  -5.250  -0.4640   0.01871   0.01088  -0.0312   1.0000   0.0705
  -5.000  -0.4408   0.01748   0.00963  -0.0307   1.0000   0.0741
  -4.750  -0.4175   0.01688   0.00903  -0.0300   1.0000   0.0774
  -4.500  -0.3935   0.01634   0.00842  -0.0294   1.0000   0.0810
  -4.250  -0.3694   0.01583   0.00784  -0.0289   1.0000   0.0852
  -4.000  -0.3456   0.01525   0.00735  -0.0286   1.0000   0.0916
  -3.750  -0.3072   0.01462   0.00675  -0.0309   0.9966   0.1021
  -3.500  -0.2664   0.01403   0.00625  -0.0339   0.9925   0.1262
  -3.250  -0.2262   0.01339   0.00589  -0.0368   0.9877   0.1752
  -3.000  -0.1855   0.01293   0.00570  -0.0399   0.9829   0.2355
  -2.750  -0.1461   0.01250   0.00553  -0.0427   0.9768   0.2996
  -2.500  -0.1068   0.01206   0.00539  -0.0453   0.9711   0.3740
  -2.250  -0.0695   0.01143   0.00529  -0.0476   0.9648   0.4935
  -2.000  -0.0338   0.01076   0.00529  -0.0490   0.9593   0.6532
  -1.750  -0.0021   0.01032   0.00529  -0.0490   0.9518   0.7741
  -1.500   0.0370   0.01009   0.00529  -0.0500   0.9481   0.8762
  -1.250   0.0814   0.01004   0.00525  -0.0525   0.9416   0.9461
  -1.000   0.1439   0.00994   0.00509  -0.0592   0.9391   0.9857
  -0.750   0.2034   0.00976   0.00482  -0.0657   0.9353   1.0000
  -0.500   0.2357   0.00959   0.00458  -0.0664   0.9227   1.0000
  -0.250   0.2659   0.00943   0.00435  -0.0666   0.9095   1.0000
   0.000   0.2938   0.00929   0.00415  -0.0663   0.8952   1.0000
   0.250   0.3200   0.00918   0.00397  -0.0656   0.8797   1.0000
   0.500   0.3453   0.00910   0.00382  -0.0647   0.8633   1.0000
   0.750   0.3704   0.00904   0.00370  -0.0637   0.8461   1.0000
   1.000   0.3954   0.00902   0.00359  -0.0627   0.8285   1.0000
   1.250   0.4200   0.00904   0.00353  -0.0616   0.8096   1.0000
   1.500   0.4445   0.00909   0.00350  -0.0606   0.7893   1.0000
   1.750   0.4693   0.00916   0.00348  -0.0597   0.7693   1.0000
   2.000   0.4941   0.00926   0.00349  -0.0587   0.7492   1.0000
   2.250   0.5187   0.00938   0.00354  -0.0578   0.7276   1.0000
   2.500   0.5436   0.00952   0.00358  -0.0569   0.7071   1.0000
   2.750   0.5684   0.00968   0.00367  -0.0561   0.6862   1.0000
   3.000   0.5932   0.00985   0.00377  -0.0552   0.6646   1.0000
   3.250   0.6180   0.01005   0.00386  -0.0544   0.6433   1.0000
   3.500   0.6423   0.01023   0.00400  -0.0535   0.6187   1.0000
   3.750   0.6668   0.01044   0.00412  -0.0526   0.5952   1.0000
   4.000   0.6911   0.01066   0.00427  -0.0517   0.5702   1.0000
   4.250   0.7151   0.01089   0.00444  -0.0508   0.5430   1.0000
   4.500   0.7387   0.01115   0.00460  -0.0499   0.5135   1.0000
   4.750   0.7623   0.01142   0.00479  -0.0489   0.4837   1.0000
   5.000   0.7860   0.01171   0.00502  -0.0481   0.4540   1.0000
   5.250   0.8092   0.01203   0.00526  -0.0472   0.4204   1.0000
   5.500   0.8318   0.01242   0.00553  -0.0462   0.3825   1.0000
   5.750   0.8537   0.01290   0.00586  -0.0451   0.3375   1.0000
   6.000   0.8740   0.01355   0.00628  -0.0439   0.2798   1.0000
   6.250   0.8916   0.01455   0.00688  -0.0425   0.2040   1.0000
   6.500   0.9062   0.01601   0.00782  -0.0407   0.1264   1.0000
   6.750   0.9231   0.01725   0.00883  -0.0390   0.0965   1.0000
   7.000   0.9421   0.01822   0.00977  -0.0377   0.0849   1.0000
   7.250   0.9591   0.01941   0.01087  -0.0361   0.0781   1.0000
   7.500   0.9803   0.02018   0.01175  -0.0349   0.0741   1.0000
   7.750   1.0006   0.02105   0.01264  -0.0338   0.0701   1.0000
   8.000   1.0186   0.02240   0.01393  -0.0324   0.0662   1.0000
   8.250   1.0399   0.02343   0.01506  -0.0314   0.0638   1.0000
   8.500   1.0613   0.02435   0.01610  -0.0304   0.0609   1.0000
   8.750   1.0820   0.02532   0.01711  -0.0294   0.0578   1.0000
   9.000   1.1028   0.02701   0.01876  -0.0287   0.0549   1.0000
   9.250   1.1235   0.02844   0.02038  -0.0277   0.0525   1.0000
   9.500   1.1436   0.02960   0.02173  -0.0266   0.0499   1.0000
   9.750   1.1626   0.03083   0.02308  -0.0255   0.0473   1.0000
  10.000   1.1818   0.03268   0.02490  -0.0248   0.0446   1.0000
  10.250   1.1973   0.03514   0.02766  -0.0234   0.0427   1.0000
  10.500   1.2111   0.03687   0.02970  -0.0216   0.0409   1.0000
  10.750   1.2238   0.03857   0.03162  -0.0199   0.0388   1.0000
  11.000   1.2361   0.04000   0.03316  -0.0183   0.0370   1.0000
  11.250   1.2478   0.04266   0.03588  -0.0172   0.0354   1.0000
  11.500   1.2451   0.04728   0.04089  -0.0146   0.0345   1.0000
  11.750   1.2394   0.04942   0.04337  -0.0111   0.0340   1.0000
  12.000   1.2283   0.05198   0.04625  -0.0075   0.0335   1.0000
  12.250   1.2140   0.05501   0.04958  -0.0045   0.0332   1.0000
  12.500   1.1974   0.05852   0.05338  -0.0024   0.0329   1.0000
  12.750   1.1785   0.06262   0.05774  -0.0014   0.0326   1.0000
  13.000   1.1572   0.06742   0.06279  -0.0015   0.0326   1.0000
  13.250   1.1338   0.07304   0.06865  -0.0030   0.0326   1.0000
  13.500   1.1081   0.07966   0.07548  -0.0058   0.0328   1.0000
  13.750   1.0810   0.08726   0.08327  -0.0099   0.0332   1.0000
  14.000   1.0529   0.09590   0.09207  -0.0150   0.0337   1.0000
  14.250   1.0245   0.10545   0.10173  -0.0206   0.0342   1.0000
  14.500   0.6680   0.14879   0.14542  -0.0292   0.0778   1.0000
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