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NACA 0015 (naca0015-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 0015 (naca0015-il)
Reynolds number: 100,000
Max Cl/Cd: 37.5 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0015-il-100000.txt
Download as CSV file: xf-naca0015-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0015                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.9918   0.07386   0.06732  -0.0434   1.0000   0.0931
 -13.500  -1.0244   0.06821   0.06144  -0.0442   1.0000   0.0930
 -13.250  -1.0543   0.06363   0.05660  -0.0433   1.0000   0.0930
 -13.000  -1.0815   0.05992   0.05262  -0.0408   1.0000   0.0931
 -12.750  -1.1060   0.05692   0.04933  -0.0370   1.0000   0.0933
 -12.500  -1.0961   0.05378   0.04619  -0.0363   1.0000   0.0949
 -12.250  -1.0894   0.05164   0.04399  -0.0348   1.0000   0.0965
 -12.000  -1.0861   0.04938   0.04158  -0.0328   1.0000   0.0979
 -11.750  -1.0855   0.04699   0.03895  -0.0304   1.0000   0.0994
 -11.500  -1.0844   0.04470   0.03639  -0.0277   1.0000   0.1012
 -11.250  -1.0839   0.04255   0.03387  -0.0248   1.0000   0.1032
 -11.000  -1.0765   0.04031   0.03136  -0.0226   1.0000   0.1055
 -10.750  -1.0559   0.03869   0.02982  -0.0220   1.0000   0.1087
 -10.500  -1.0416   0.03713   0.02812  -0.0204   1.0000   0.1121
 -10.250  -1.0304   0.03553   0.02621  -0.0181   1.0000   0.1157
 -10.000  -1.0105   0.03385   0.02459  -0.0173   1.0000   0.1202
  -9.750  -0.9937   0.03268   0.02338  -0.0158   1.0000   0.1255
  -9.500  -0.9786   0.03123   0.02173  -0.0139   1.0000   0.1312
  -9.250  -0.9588   0.03010   0.02075  -0.0129   1.0000   0.1379
  -9.000  -0.9434   0.02889   0.01942  -0.0109   1.0000   0.1458
  -8.750  -0.9265   0.02794   0.01855  -0.0093   1.0000   0.1546
  -8.500  -0.9100   0.02689   0.01755  -0.0075   1.0000   0.1642
  -8.250  -0.8950   0.02597   0.01658  -0.0055   1.0000   0.1755
  -8.000  -0.8797   0.02519   0.01582  -0.0034   1.0000   0.1877
  -7.750  -0.8638   0.02437   0.01512  -0.0015   1.0000   0.2008
  -7.500  -0.8484   0.02362   0.01445   0.0006   1.0000   0.2150
  -7.250  -0.8331   0.02292   0.01383   0.0027   1.0000   0.2306
  -7.000  -0.8179   0.02228   0.01327   0.0048   1.0000   0.2475
  -6.750  -0.8025   0.02169   0.01274   0.0069   1.0000   0.2658
  -6.500  -0.7870   0.02114   0.01225   0.0090   1.0000   0.2854
  -6.250  -0.7712   0.02062   0.01179   0.0110   1.0000   0.3061
  -6.000  -0.7545   0.02012   0.01145   0.0130   1.0000   0.3266
  -5.750  -0.7377   0.01969   0.01113   0.0149   1.0000   0.3481
  -5.500  -0.7206   0.01930   0.01083   0.0167   1.0000   0.3708
  -5.250  -0.7032   0.01895   0.01053   0.0185   1.0000   0.3942
  -5.000  -0.6848   0.01863   0.01034   0.0201   1.0000   0.4163
  -4.750  -0.6664   0.01836   0.01018   0.0217   1.0000   0.4396
  -4.500  -0.6478   0.01813   0.00999   0.0233   1.0000   0.4642
  -4.250  -0.6283   0.01792   0.00992   0.0247   1.0000   0.4871
  -4.000  -0.6087   0.01777   0.00989   0.0261   1.0000   0.5110
  -3.750  -0.5892   0.01765   0.00983   0.0274   1.0000   0.5363
  -3.500  -0.5693   0.01756   0.00987   0.0287   1.0000   0.5598
  -3.250  -0.5497   0.01751   0.00994   0.0300   1.0000   0.5841
  -3.000  -0.5304   0.01749   0.00999   0.0312   1.0000   0.6100
  -2.750  -0.5110   0.01752   0.01017   0.0325   1.0000   0.6335
  -2.500  -0.4865   0.01761   0.01037   0.0328   0.9982   0.6598
  -2.250  -0.4391   0.01785   0.01072   0.0289   0.9882   0.6899
  -2.000  -0.3925   0.01807   0.01101   0.0253   0.9775   0.7205
  -1.750  -0.3443   0.01834   0.01141   0.0219   0.9674   0.7471
  -1.500  -0.3021   0.01848   0.01160   0.0195   0.9547   0.7742
  -1.250  -0.2605   0.01867   0.01187   0.0176   0.9418   0.7975
  -1.000  -0.2161   0.01890   0.01215   0.0153   0.9299   0.8195
  -0.750  -0.1605   0.01912   0.01239   0.0111   0.9210   0.8397
  -0.500  -0.1125   0.01931   0.01260   0.0084   0.9083   0.8575
  -0.250  -0.0557   0.01942   0.01272   0.0041   0.8982   0.8727
   0.000   0.0000   0.01941   0.01270   0.0000   0.8869   0.8869
   0.250   0.0556   0.01942   0.01272  -0.0041   0.8727   0.8983
   0.500   0.1126   0.01931   0.01260  -0.0084   0.8575   0.9083
   0.750   0.1605   0.01912   0.01239  -0.0111   0.8397   0.9210
   1.000   0.2160   0.01890   0.01215  -0.0153   0.8195   0.9299
   1.250   0.2605   0.01867   0.01187  -0.0176   0.7975   0.9418
   1.500   0.3021   0.01848   0.01160  -0.0195   0.7743   0.9547
   1.750   0.3442   0.01834   0.01140  -0.0218   0.7471   0.9675
   2.000   0.3925   0.01807   0.01101  -0.0253   0.7205   0.9775
   2.250   0.4391   0.01785   0.01072  -0.0289   0.6899   0.9882
   2.500   0.4865   0.01761   0.01037  -0.0328   0.6598   0.9982
   2.750   0.5109   0.01752   0.01016  -0.0325   0.6336   1.0000
   3.000   0.5303   0.01749   0.00998  -0.0312   0.6101   1.0000
   3.250   0.5496   0.01751   0.00994  -0.0300   0.5842   1.0000
   3.500   0.5692   0.01755   0.00987  -0.0286   0.5598   1.0000
   3.750   0.5890   0.01765   0.00982  -0.0273   0.5363   1.0000
   4.000   0.6085   0.01777   0.00988  -0.0260   0.5110   1.0000
   4.250   0.6281   0.01792   0.00992  -0.0247   0.4872   1.0000
   4.500   0.6477   0.01813   0.00999  -0.0233   0.4642   1.0000
   4.750   0.6663   0.01835   0.01018  -0.0217   0.4396   1.0000
   5.000   0.6847   0.01862   0.01034  -0.0201   0.4164   1.0000
   5.250   0.7030   0.01895   0.01052  -0.0185   0.3942   1.0000
   5.500   0.7205   0.01930   0.01082  -0.0167   0.3709   1.0000
   5.750   0.7376   0.01969   0.01113  -0.0148   0.3481   1.0000
   6.000   0.7544   0.02012   0.01145  -0.0129   0.3266   1.0000
   6.250   0.7711   0.02062   0.01179  -0.0110   0.3062   1.0000
   6.500   0.7869   0.02113   0.01225  -0.0090   0.2855   1.0000
   6.750   0.8024   0.02169   0.01274  -0.0069   0.2658   1.0000
   7.000   0.8178   0.02228   0.01327  -0.0048   0.2475   1.0000
   7.250   0.8330   0.02292   0.01383  -0.0026   0.2306   1.0000
   7.500   0.8483   0.02361   0.01445  -0.0005   0.2150   1.0000
   7.750   0.8637   0.02437   0.01512   0.0015   0.2008   1.0000
   8.000   0.8796   0.02519   0.01581   0.0034   0.1877   1.0000
   8.250   0.8949   0.02597   0.01657   0.0055   0.1755   1.0000
   8.500   0.9100   0.02689   0.01754   0.0075   0.1642   1.0000
   8.750   0.9265   0.02794   0.01855   0.0093   0.1546   1.0000
   9.000   0.9434   0.02889   0.01941   0.0109   0.1458   1.0000
   9.250   0.9588   0.03010   0.02075   0.0128   0.1379   1.0000
   9.500   0.9786   0.03123   0.02173   0.0139   0.1312   1.0000
   9.750   0.9938   0.03268   0.02338   0.0158   0.1255   1.0000
  10.000   1.0106   0.03385   0.02459   0.0173   0.1202   1.0000
  10.250   1.0305   0.03553   0.02621   0.0181   0.1157   1.0000
  10.500   1.0417   0.03713   0.02812   0.0203   0.1120   1.0000
  10.750   1.0561   0.03869   0.02982   0.0220   0.1087   1.0000
  11.000   1.0768   0.04032   0.03136   0.0225   0.1055   1.0000
  11.250   1.0841   0.04256   0.03387   0.0247   0.1032   1.0000
  11.500   1.0847   0.04471   0.03639   0.0277   0.1012   1.0000
  11.750   1.0858   0.04699   0.03896   0.0303   0.0993   1.0000
  12.000   1.0865   0.04938   0.04159   0.0327   0.0979   1.0000
  12.250   1.0902   0.05164   0.04399   0.0346   0.0964   1.0000
  12.500   1.0972   0.05379   0.04620   0.0362   0.0949   1.0000
  12.750   1.1063   0.05695   0.04936   0.0369   0.0933   1.0000
  13.000   1.0817   0.05995   0.05265   0.0407   0.0931   1.0000
  13.250   1.0546   0.06367   0.05665   0.0431   0.0929   1.0000
  13.500   1.0247   0.06828   0.06152   0.0440   0.0930   1.0000
  13.750   0.9920   0.07396   0.06743   0.0432   0.0931   1.0000
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