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NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 642-015 AIRFOIL (n64015-il)
Reynolds number: 200,000
Max Cl/Cd: 48.85 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64015-il-200000.txt
Download as CSV file: xf-n64015-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015 AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7315   0.09111   0.08743  -0.0265   1.0000   0.0465
 -13.750  -0.7239   0.08683   0.08314  -0.0267   1.0000   0.0452
 -13.500  -0.8633   0.08080   0.07661  -0.0310   1.0000   0.0452
 -13.250  -0.8831   0.07497   0.07066  -0.0331   1.0000   0.0446
 -13.000  -0.9058   0.06941   0.06494  -0.0347   1.0000   0.0439
 -12.750  -0.9298   0.06418   0.05951  -0.0355   1.0000   0.0431
 -12.500  -0.9561   0.05913   0.05419  -0.0353   1.0000   0.0421
 -12.250  -1.0083   0.05275   0.04719  -0.0327   1.0000   0.0402
 -12.000  -1.0342   0.04944   0.04345  -0.0291   1.0000   0.0396
 -11.750  -1.0406   0.04690   0.04061  -0.0263   1.0000   0.0393
 -11.500  -1.0368   0.04412   0.03758  -0.0245   1.0000   0.0394
 -11.250  -1.0267   0.04134   0.03459  -0.0235   1.0000   0.0396
 -11.000  -1.0122   0.03887   0.03195  -0.0227   1.0000   0.0400
 -10.750  -0.9954   0.03699   0.02997  -0.0221   1.0000   0.0408
 -10.500  -0.9774   0.03556   0.02849  -0.0215   1.0000   0.0421
 -10.250  -0.9594   0.03384   0.02658  -0.0208   1.0000   0.0431
 -10.000  -0.9390   0.03205   0.02460  -0.0202   1.0000   0.0440
  -9.750  -0.9168   0.03044   0.02281  -0.0198   1.0000   0.0450
  -9.500  -0.8948   0.02914   0.02132  -0.0193   1.0000   0.0459
  -9.250  -0.8623   0.02702   0.01919  -0.0203   1.0000   0.0476
  -9.000  -0.8386   0.02588   0.01811  -0.0203   1.0000   0.0498
  -8.750  -0.8177   0.02496   0.01717  -0.0197   1.0000   0.0523
  -8.500  -0.7959   0.02405   0.01620  -0.0192   1.0000   0.0544
  -8.250  -0.7756   0.02270   0.01489  -0.0186   1.0000   0.0570
  -8.000  -0.7630   0.02188   0.01415  -0.0170   1.0000   0.0595
  -7.750  -0.7642   0.02151   0.01379  -0.0131   0.9986   0.0620
  -7.500  -0.7285   0.02023   0.01251  -0.0160   0.9864   0.0677
  -7.250  -0.6929   0.01916   0.01144  -0.0188   0.9755   0.0752
  -7.000  -0.6623   0.01797   0.01029  -0.0208   0.9631   0.0869
  -6.750  -0.6390   0.01678   0.00922  -0.0213   0.9488   0.1077
  -6.500  -0.6292   0.01537   0.00822  -0.0194   0.9323   0.1689
  -6.250  -0.6305   0.01368   0.00730  -0.0155   0.9160   0.3045
  -6.000  -0.6248   0.01279   0.00711  -0.0120   0.9024   0.4478
  -5.750  -0.6053   0.01277   0.00714  -0.0101   0.8920   0.5002
  -5.500  -0.5837   0.01283   0.00716  -0.0086   0.8824   0.5290
  -5.250  -0.5605   0.01293   0.00716  -0.0075   0.8721   0.5512
  -5.000  -0.5373   0.01304   0.00717  -0.0062   0.8641   0.5686
  -4.750  -0.5121   0.01316   0.00725  -0.0054   0.8545   0.5836
  -4.500  -0.4874   0.01333   0.00737  -0.0043   0.8472   0.5981
  -4.250  -0.4616   0.01354   0.00758  -0.0035   0.8381   0.6127
  -4.000  -0.4363   0.01376   0.00776  -0.0025   0.8312   0.6255
  -3.750  -0.4102   0.01395   0.00792  -0.0018   0.8221   0.6382
  -3.250  -0.3575   0.01433   0.00827  -0.0003   0.8071   0.6594
  -3.000  -0.3317   0.01425   0.00803   0.0001   0.8008   0.6671
  -2.750  -0.3037   0.01422   0.00801   0.0002   0.7932   0.6712
  -2.500  -0.2765   0.01416   0.00788   0.0003   0.7865   0.6761
  -2.250  -0.2497   0.01405   0.00764   0.0003   0.7804   0.6824
  -2.000  -0.2219   0.01400   0.00760   0.0004   0.7728   0.6865
  -1.750  -0.1946   0.01397   0.00751   0.0007   0.7672   0.6914
  -1.500  -0.1670   0.01391   0.00739   0.0004   0.7602   0.6974
  -1.250  -0.1393   0.01382   0.00727   0.0004   0.7541   0.7017
  -1.000  -0.1116   0.01380   0.00721   0.0006   0.7495   0.7059
  -0.750  -0.0836   0.01379   0.00721   0.0003   0.7426   0.7114
  -0.500  -0.0557   0.01371   0.00708   0.0001   0.7371   0.7169
  -0.250  -0.0279   0.01370   0.00704   0.0002   0.7328   0.7208
   0.000   0.0000   0.01372   0.00712   0.0000   0.7260   0.7260
   0.250   0.0279   0.01370   0.00704  -0.0002   0.7208   0.7328
   0.500   0.0558   0.01371   0.00708  -0.0001   0.7169   0.7371
   0.750   0.0836   0.01379   0.00721  -0.0003   0.7113   0.7426
   1.000   0.1116   0.01380   0.00721  -0.0006   0.7059   0.7495
   1.250   0.1393   0.01382   0.00727  -0.0004   0.7017   0.7541
   1.500   0.1670   0.01391   0.00739  -0.0004   0.6974   0.7602
   1.750   0.1946   0.01397   0.00751  -0.0007   0.6914   0.7672
   2.000   0.2219   0.01400   0.00760  -0.0004   0.6865   0.7728
   2.250   0.2498   0.01405   0.00764  -0.0003   0.6824   0.7804
   2.500   0.2765   0.01416   0.00788  -0.0004   0.6761   0.7865
   2.750   0.3038   0.01422   0.00801  -0.0002   0.6711   0.7933
   3.000   0.3317   0.01425   0.00803  -0.0001   0.6671   0.8008
   3.250   0.3575   0.01433   0.00827   0.0002   0.6594   0.8071
   3.750   0.4102   0.01395   0.00793   0.0017   0.6382   0.8221
   4.000   0.4363   0.01376   0.00776   0.0025   0.6255   0.8312
   4.250   0.4617   0.01354   0.00758   0.0035   0.6126   0.8381
   4.500   0.4874   0.01333   0.00737   0.0043   0.5980   0.8472
   4.750   0.5122   0.01316   0.00725   0.0054   0.5836   0.8545
   5.000   0.5373   0.01304   0.00716   0.0062   0.5685   0.8641
   5.250   0.5605   0.01293   0.00716   0.0075   0.5514   0.8721
   5.500   0.5837   0.01283   0.00716   0.0086   0.5290   0.8824
   5.750   0.6054   0.01276   0.00713   0.0101   0.5000   0.8920
   6.000   0.6248   0.01279   0.00711   0.0120   0.4475   0.9025
   6.250   0.6306   0.01368   0.00730   0.0155   0.3049   0.9160
   6.500   0.6291   0.01538   0.00822   0.0194   0.1684   0.9324
   6.750   0.6391   0.01678   0.00922   0.0213   0.1076   0.9488
   7.000   0.6624   0.01797   0.01029   0.0208   0.0870   0.9631
   7.250   0.6931   0.01916   0.01144   0.0188   0.0752   0.9755
   7.500   0.7286   0.02023   0.01251   0.0160   0.0676   0.9865
   7.750   0.7644   0.02152   0.01380   0.0131   0.0618   0.9987
   8.000   0.7630   0.02188   0.01415   0.0170   0.0594   1.0000
   8.250   0.7757   0.02272   0.01491   0.0186   0.0569   1.0000
   8.500   0.7961   0.02406   0.01620   0.0192   0.0544   1.0000
   8.750   0.8179   0.02496   0.01717   0.0197   0.0523   1.0000
   9.000   0.8392   0.02590   0.01813   0.0202   0.0499   1.0000
   9.250   0.8624   0.02701   0.01918   0.0203   0.0477   1.0000
   9.500   0.8945   0.02912   0.02130   0.0193   0.0459   1.0000
   9.750   0.9167   0.03043   0.02279   0.0198   0.0449   1.0000
  10.000   0.9390   0.03206   0.02462   0.0203   0.0439   1.0000
  10.250   0.9595   0.03383   0.02657   0.0208   0.0431   1.0000
  10.500   0.9776   0.03555   0.02848   0.0215   0.0421   1.0000
  10.750   0.9954   0.03705   0.03005   0.0221   0.0409   1.0000
  11.000   1.0124   0.03892   0.03200   0.0227   0.0400   1.0000
  11.250   1.0278   0.04145   0.03467   0.0233   0.0394   1.0000
  11.500   1.0373   0.04419   0.03765   0.0245   0.0393   1.0000
  11.750   1.0417   0.04713   0.04084   0.0260   0.0392   1.0000
  12.000   1.0347   0.04947   0.04348   0.0290   0.0395   1.0000
  12.250   0.9934   0.05364   0.04825   0.0335   0.0408   1.0000
  12.500   0.9561   0.05920   0.05426   0.0353   0.0421   1.0000
  12.750   0.9293   0.06433   0.05966   0.0354   0.0431   1.0000
  13.000   0.9056   0.06950   0.06504   0.0346   0.0439   1.0000
  13.250   0.8832   0.07505   0.07074   0.0330   0.0446   1.0000
  13.500   0.8639   0.08092   0.07673   0.0309   0.0453   1.0000
  13.750   0.7233   0.08667   0.08299   0.0268   0.0452   1.0000
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