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NACA 1412 (naca1412-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 1412 (naca1412-il)
Reynolds number: 100,000
Max Cl/Cd: 44.07 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1412-il-100000.txt
Download as CSV file: xf-naca1412-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1412                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.7131   0.07555   0.07014  -0.0405   1.0000   0.0995
 -10.250  -0.7225   0.07035   0.06491  -0.0414   1.0000   0.0980
 -10.000  -0.7491   0.06473   0.05918  -0.0416   1.0000   0.0962
  -9.750  -0.7792   0.05833   0.05251  -0.0411   1.0000   0.0941
  -9.500  -0.7976   0.05289   0.04670  -0.0395   1.0000   0.0932
  -9.250  -0.8037   0.04875   0.04221  -0.0375   1.0000   0.0937
  -9.000  -0.8042   0.04510   0.03819  -0.0354   1.0000   0.0946
  -8.750  -0.8011   0.04172   0.03440  -0.0331   1.0000   0.0954
  -8.500  -0.7942   0.03869   0.03095  -0.0308   1.0000   0.0964
  -8.250  -0.7844   0.03626   0.02807  -0.0285   1.0000   0.0985
  -8.000  -0.7728   0.03437   0.02565  -0.0261   1.0000   0.1005
  -7.750  -0.7556   0.03177   0.02298  -0.0249   1.0000   0.1029
  -7.500  -0.7370   0.03013   0.02124  -0.0235   1.0000   0.1054
  -7.250  -0.7180   0.02874   0.01969  -0.0221   1.0000   0.1090
  -7.000  -0.6993   0.02747   0.01809  -0.0204   1.0000   0.1134
  -6.750  -0.6788   0.02583   0.01643  -0.0193   1.0000   0.1176
  -6.500  -0.6579   0.02469   0.01527  -0.0180   1.0000   0.1228
  -6.250  -0.6372   0.02360   0.01395  -0.0166   1.0000   0.1294
  -6.000  -0.6166   0.02252   0.01305  -0.0155   1.0000   0.1384
  -5.750  -0.5962   0.02150   0.01205  -0.0142   1.0000   0.1495
  -5.500  -0.5758   0.02055   0.01116  -0.0129   1.0000   0.1639
  -5.250  -0.5560   0.01973   0.01045  -0.0115   1.0000   0.1833
  -5.000  -0.5362   0.01896   0.00980  -0.0103   1.0000   0.2081
  -4.750  -0.5162   0.01831   0.00927  -0.0090   1.0000   0.2378
  -4.500  -0.4964   0.01769   0.00888  -0.0079   1.0000   0.2717
  -4.250  -0.4763   0.01715   0.00856  -0.0067   1.0000   0.3108
  -4.000  -0.4559   0.01666   0.00831  -0.0056   1.0000   0.3547
  -3.750  -0.4350   0.01623   0.00811  -0.0046   1.0000   0.4022
  -3.500  -0.4139   0.01585   0.00798  -0.0036   1.0000   0.4520
  -3.250  -0.3927   0.01553   0.00792  -0.0024   1.0000   0.5038
  -3.000  -0.3718   0.01528   0.00792  -0.0012   1.0000   0.5582
  -2.750  -0.3512   0.01510   0.00799   0.0002   1.0000   0.6146
  -2.500  -0.3315   0.01500   0.00815   0.0019   1.0000   0.6711
  -2.250  -0.3127   0.01499   0.00834   0.0039   1.0000   0.7291
  -2.000  -0.2958   0.01508   0.00863   0.0066   1.0000   0.7850
  -1.750  -0.2796   0.01528   0.00898   0.0094   1.0000   0.8424
  -1.500  -0.2488   0.01568   0.00943   0.0096   0.9971   0.9014
  -1.250  -0.1819   0.01628   0.00995   0.0026   0.9909   0.9512
  -1.000  -0.0985   0.01681   0.01032  -0.0082   0.9873   0.9817
  -0.750  -0.0100   0.01707   0.01045  -0.0205   0.9846   1.0000
  -0.500   0.0466   0.01700   0.01028  -0.0274   0.9724   1.0000
  -0.250   0.1020   0.01688   0.01011  -0.0336   0.9598   1.0000
   0.000   0.1566   0.01672   0.00990  -0.0394   0.9466   1.0000
   0.250   0.2111   0.01648   0.00964  -0.0449   0.9332   1.0000
   0.500   0.2607   0.01617   0.00932  -0.0491   0.9183   1.0000
   0.750   0.3044   0.01582   0.00897  -0.0519   0.9016   1.0000
   1.000   0.3417   0.01548   0.00863  -0.0532   0.8834   1.0000
   1.250   0.3736   0.01516   0.00829  -0.0534   0.8646   1.0000
   1.500   0.3975   0.01500   0.00810  -0.0521   0.8425   1.0000
   1.750   0.4213   0.01484   0.00791  -0.0506   0.8208   1.0000
   2.000   0.4453   0.01470   0.00771  -0.0491   0.8001   1.0000
   2.250   0.4667   0.01468   0.00765  -0.0473   0.7767   1.0000
   2.500   0.4890   0.01466   0.00756  -0.0456   0.7539   1.0000
   2.750   0.5114   0.01468   0.00750  -0.0439   0.7311   1.0000
   3.000   0.5331   0.01477   0.00754  -0.0422   0.7069   1.0000
   3.250   0.5562   0.01486   0.00752  -0.0406   0.6846   1.0000
   3.500   0.5775   0.01503   0.00765  -0.0390   0.6593   1.0000
   3.750   0.6002   0.01517   0.00768  -0.0374   0.6358   1.0000
   4.000   0.6214   0.01537   0.00784  -0.0358   0.6092   1.0000
   4.250   0.6432   0.01558   0.00795  -0.0342   0.5834   1.0000
   4.500   0.6646   0.01581   0.00811  -0.0325   0.5566   1.0000
   4.750   0.6856   0.01608   0.00831  -0.0309   0.5288   1.0000
   5.000   0.7065   0.01637   0.00851  -0.0293   0.5007   1.0000
   5.250   0.7269   0.01668   0.00871  -0.0276   0.4709   1.0000
   5.500   0.7464   0.01700   0.00896  -0.0257   0.4378   1.0000
   5.750   0.7650   0.01736   0.00922  -0.0239   0.4009   1.0000
   6.000   0.7830   0.01779   0.00949  -0.0219   0.3624   1.0000
   6.250   0.8005   0.01834   0.00989  -0.0200   0.3216   1.0000
   6.500   0.8171   0.01906   0.01038  -0.0181   0.2815   1.0000
   6.750   0.8334   0.01994   0.01106  -0.0162   0.2412   1.0000
   7.000   0.8491   0.02100   0.01187  -0.0143   0.2062   1.0000
   7.250   0.8652   0.02218   0.01285  -0.0125   0.1769   1.0000
   7.500   0.8821   0.02347   0.01393  -0.0109   0.1552   1.0000
   7.750   0.9013   0.02478   0.01515  -0.0095   0.1395   1.0000
   8.000   0.9227   0.02627   0.01643  -0.0086   0.1284   1.0000
   8.250   0.9440   0.02742   0.01775  -0.0074   0.1197   1.0000
   8.500   0.9672   0.02901   0.01923  -0.0069   0.1129   1.0000
   8.750   0.9891   0.03040   0.02084  -0.0059   0.1076   1.0000
   9.000   1.0124   0.03194   0.02240  -0.0053   0.1035   1.0000
   9.250   1.0363   0.03417   0.02462  -0.0050   0.0998   1.0000
   9.500   1.0535   0.03579   0.02663  -0.0035   0.0966   1.0000
   9.750   1.0716   0.03765   0.02874  -0.0022   0.0936   1.0000
  10.000   1.0893   0.03971   0.03098  -0.0011   0.0914   1.0000
  10.250   1.1076   0.04195   0.03330  -0.0003   0.0889   1.0000
  10.500   1.1188   0.04512   0.03673   0.0012   0.0870   1.0000
  10.750   1.1212   0.04766   0.03977   0.0039   0.0856   1.0000
  11.000   1.1210   0.05082   0.04336   0.0065   0.0848   1.0000
  11.250   1.1155   0.05423   0.04717   0.0092   0.0841   1.0000
  11.500   1.1039   0.05780   0.05111   0.0120   0.0836   1.0000
  11.750   1.0846   0.06140   0.05500   0.0152   0.0834   1.0000
  12.000   1.0593   0.06544   0.05930   0.0177   0.0835   1.0000
  12.250   1.0298   0.07040   0.06450   0.0184   0.0840   1.0000
  12.500   0.9970   0.07656   0.07086   0.0171   0.0849   1.0000
  12.750   0.9639   0.08402   0.07846   0.0139   0.0859   1.0000
  13.000   0.9351   0.09232   0.08686   0.0098   0.0868   1.0000
  13.250   0.9158   0.10047   0.09505   0.0063   0.0876   1.0000
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