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NACA 1410 (naca1410-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 1410 (naca1410-il)
Reynolds number: 100,000
Max Cl/Cd: 44.56 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1410-il-100000.txt
Download as CSV file: xf-naca1410-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1410                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6299   0.09111   0.08620  -0.0171   1.0000   0.1657
  -8.750  -0.7041   0.06367   0.05824  -0.0347   1.0000   0.0925
  -8.500  -0.7018   0.05859   0.05305  -0.0346   1.0000   0.0911
  -8.250  -0.7037   0.05311   0.04732  -0.0344   1.0000   0.0890
  -8.000  -0.7070   0.04703   0.04077  -0.0335   1.0000   0.0862
  -7.750  -0.7062   0.04131   0.03438  -0.0319   1.0000   0.0840
  -7.500  -0.6931   0.03851   0.03128  -0.0305   1.0000   0.0865
  -7.250  -0.6799   0.03562   0.02795  -0.0288   1.0000   0.0892
  -7.000  -0.6647   0.03274   0.02456  -0.0271   1.0000   0.0908
  -6.750  -0.6474   0.03083   0.02204  -0.0252   1.0000   0.0935
  -6.500  -0.6280   0.02834   0.01950  -0.0243   1.0000   0.0974
  -6.250  -0.6066   0.02669   0.01767  -0.0232   1.0000   0.1006
  -6.000  -0.5848   0.02523   0.01593  -0.0219   1.0000   0.1049
  -5.750  -0.5626   0.02370   0.01422  -0.0208   1.0000   0.1098
  -5.500  -0.5399   0.02244   0.01297  -0.0199   1.0000   0.1149
  -5.250  -0.5166   0.02134   0.01165  -0.0187   1.0000   0.1210
  -5.000  -0.4942   0.02011   0.01056  -0.0178   1.0000   0.1292
  -4.750  -0.4721   0.01914   0.00963  -0.0167   1.0000   0.1423
  -4.500  -0.4503   0.01814   0.00875  -0.0155   1.0000   0.1616
  -4.250  -0.4291   0.01710   0.00790  -0.0143   1.0000   0.1948
  -4.000  -0.4085   0.01614   0.00731  -0.0132   1.0000   0.2460
  -3.750  -0.3877   0.01528   0.00680  -0.0122   1.0000   0.3130
  -3.500  -0.3677   0.01439   0.00649  -0.0110   1.0000   0.3976
  -3.250  -0.3476   0.01385   0.00642  -0.0095   1.0000   0.5100
  -3.000  -0.3279   0.01338   0.00639  -0.0075   1.0000   0.6047
  -2.750  -0.3082   0.01309   0.00642  -0.0052   1.0000   0.6866
  -2.500  -0.2887   0.01295   0.00649  -0.0027   1.0000   0.7575
  -2.250  -0.2694   0.01293   0.00662   0.0001   1.0000   0.8252
  -2.000  -0.2435   0.01306   0.00681   0.0018   1.0000   0.8935
  -1.750  -0.1878   0.01335   0.00698  -0.0027   1.0000   0.9568
  -1.500  -0.1015   0.01354   0.00694  -0.0140   1.0000   0.9933
  -1.250  -0.0874   0.01339   0.00668  -0.0133   1.0000   1.0000
  -1.000  -0.0890   0.01337   0.00657  -0.0094   1.0000   1.0000
  -0.750  -0.0809   0.01349   0.00659  -0.0071   1.0000   1.0000
  -0.500  -0.0678   0.01371   0.00672  -0.0056   1.0000   1.0000
  -0.250  -0.0483   0.01401   0.00694  -0.0053   0.9988   1.0000
   0.000   0.0079   0.01436   0.00721  -0.0117   0.9875   1.0000
   0.250   0.0634   0.01464   0.00744  -0.0179   0.9756   1.0000
   0.500   0.1185   0.01481   0.00760  -0.0237   0.9628   1.0000
   0.750   0.1732   0.01487   0.00767  -0.0292   0.9491   1.0000
   1.000   0.2291   0.01482   0.00766  -0.0348   0.9349   1.0000
   1.250   0.2826   0.01464   0.00755  -0.0395   0.9198   1.0000
   1.500   0.3308   0.01440   0.00738  -0.0430   0.9031   1.0000
   1.750   0.3711   0.01417   0.00719  -0.0446   0.8840   1.0000
   2.000   0.4027   0.01399   0.00704  -0.0444   0.8612   1.0000
   2.250   0.4326   0.01380   0.00687  -0.0438   0.8387   1.0000
   2.500   0.4581   0.01369   0.00676  -0.0422   0.8130   1.0000
   2.750   0.4818   0.01366   0.00671  -0.0404   0.7858   1.0000
   3.000   0.5054   0.01367   0.00668  -0.0387   0.7580   1.0000
   3.250   0.5287   0.01372   0.00668  -0.0369   0.7291   1.0000
   3.500   0.5514   0.01382   0.00671  -0.0350   0.6980   1.0000
   3.750   0.5739   0.01397   0.00679  -0.0332   0.6650   1.0000
   4.000   0.5964   0.01416   0.00690  -0.0315   0.6316   1.0000
   4.250   0.6188   0.01439   0.00702  -0.0298   0.5972   1.0000
   4.500   0.6400   0.01463   0.00718  -0.0280   0.5556   1.0000
   4.750   0.6605   0.01491   0.00730  -0.0261   0.5084   1.0000
   5.000   0.6805   0.01527   0.00747  -0.0243   0.4580   1.0000
   5.250   0.7005   0.01572   0.00778  -0.0226   0.4025   1.0000
   5.500   0.7189   0.01637   0.00814  -0.0208   0.3340   1.0000
   5.750   0.7346   0.01749   0.00877  -0.0188   0.2490   1.0000
   6.000   0.7492   0.01913   0.00985  -0.0168   0.1791   1.0000
   6.250   0.7667   0.02064   0.01105  -0.0151   0.1466   1.0000
   6.500   0.7867   0.02202   0.01224  -0.0138   0.1295   1.0000
   6.750   0.8092   0.02321   0.01342  -0.0128   0.1178   1.0000
   7.000   0.8331   0.02473   0.01492  -0.0120   0.1108   1.0000
   7.250   0.8578   0.02612   0.01638  -0.0113   0.1050   1.0000
   7.500   0.8826   0.02802   0.01822  -0.0109   0.0996   1.0000
   7.750   0.9059   0.02945   0.01995  -0.0099   0.0948   1.0000
   8.000   0.9293   0.03123   0.02190  -0.0092   0.0911   1.0000
   8.250   0.9522   0.03403   0.02465  -0.0089   0.0869   1.0000
   8.500   0.9697   0.03575   0.02693  -0.0071   0.0839   1.0000
   8.750   0.9862   0.03829   0.02993  -0.0055   0.0814   1.0000
   9.000   1.0032   0.04048   0.03238  -0.0043   0.0778   1.0000
   9.250   1.0205   0.04340   0.03531  -0.0036   0.0746   1.0000
   9.500   1.0278   0.04797   0.04029  -0.0019   0.0735   1.0000
   9.750   1.0294   0.05126   0.04416   0.0006   0.0726   1.0000
  10.000   1.0255   0.05510   0.04852   0.0031   0.0718   1.0000
  10.250   1.0169   0.05937   0.05322   0.0053   0.0713   1.0000
  10.500   1.0042   0.06396   0.05813   0.0072   0.0715   1.0000
  10.750   0.9889   0.06865   0.06305   0.0088   0.0721   1.0000
  11.000   0.9729   0.07343   0.06797   0.0100   0.0728   1.0000
  11.250   0.9687   0.07868   0.07332   0.0102   0.0742   1.0000
  11.500   0.6842   0.10055   0.09574  -0.0010   0.1018   1.0000
  11.750   0.6961   0.10314   0.09836   0.0011   0.1008   1.0000
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