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NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-112 (naca641112-il)
Reynolds number: 50,000
Max Cl/Cd: 29.32 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca641112-il-50000-n5.txt
Download as CSV file: xf-naca641112-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-112                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6383   0.10078   0.09348  -0.0219   1.0000   0.0542
 -11.250  -0.6502   0.09394   0.08665  -0.0263   1.0000   0.0539
 -11.000  -0.6647   0.08749   0.08018  -0.0304   1.0000   0.0536
 -10.750  -0.6810   0.08160   0.07425  -0.0339   1.0000   0.0532
 -10.500  -0.6991   0.07635   0.06893  -0.0366   1.0000   0.0528
 -10.250  -0.7182   0.07181   0.06427  -0.0380   1.0000   0.0526
 -10.000  -0.7361   0.06797   0.06030  -0.0379   1.0000   0.0526
  -9.750  -0.7492   0.06432   0.05644  -0.0373   1.0000   0.0526
  -9.500  -0.7576   0.06064   0.05249  -0.0364   1.0000   0.0528
  -9.250  -0.7611   0.05705   0.04858  -0.0354   1.0000   0.0529
  -9.000  -0.7598   0.05358   0.04475  -0.0342   1.0000   0.0531
  -8.750  -0.7547   0.05026   0.04102  -0.0330   1.0000   0.0534
  -8.500  -0.7459   0.04713   0.03746  -0.0318   1.0000   0.0539
  -8.250  -0.7338   0.04433   0.03418  -0.0305   1.0000   0.0547
  -8.000  -0.7170   0.04175   0.03156  -0.0299   1.0000   0.0567
  -7.750  -0.6992   0.03975   0.02939  -0.0291   1.0000   0.0594
  -7.500  -0.6799   0.03769   0.02707  -0.0282   1.0000   0.0619
  -7.250  -0.6578   0.03564   0.02472  -0.0273   1.0000   0.0640
  -7.000  -0.6340   0.03390   0.02265  -0.0263   1.0000   0.0666
  -6.750  -0.6117   0.03229   0.02118  -0.0255   1.0000   0.0711
  -6.500  -0.5894   0.03104   0.01980  -0.0244   1.0000   0.0762
  -6.250  -0.5673   0.02985   0.01847  -0.0230   1.0000   0.0805
  -6.000  -0.5524   0.02874   0.01745  -0.0211   1.0000   0.0867
  -5.750  -0.5391   0.02780   0.01643  -0.0189   1.0000   0.0945
  -5.500  -0.5298   0.02678   0.01547  -0.0164   1.0000   0.1021
  -5.250  -0.5218   0.02579   0.01449  -0.0137   1.0000   0.1125
  -5.000  -0.5148   0.02474   0.01356  -0.0110   1.0000   0.1299
  -4.750  -0.5087   0.02345   0.01254  -0.0085   1.0000   0.1621
  -4.500  -0.5058   0.02147   0.01144  -0.0061   1.0000   0.2710
  -4.250  -0.5041   0.02053   0.01178  -0.0016   1.0000   0.4948
  -4.000  -0.4773   0.02092   0.01228  -0.0006   0.9901   0.5980
  -3.750  -0.4505   0.02197   0.01337   0.0018   0.9794   0.6680
  -3.500  -0.4250   0.02327   0.01464   0.0053   0.9696   0.7210
  -3.250  -0.3907   0.02400   0.01521   0.0060   0.9619   0.7480
  -3.000  -0.3571   0.02403   0.01497   0.0050   0.9524   0.7611
  -2.750  -0.3221   0.02393   0.01464   0.0032   0.9436   0.7722
  -2.500  -0.2852   0.02382   0.01432   0.0010   0.9355   0.7832
  -2.250  -0.2503   0.02378   0.01410  -0.0004   0.9267   0.7916
  -2.000  -0.2128   0.02364   0.01378  -0.0028   0.9193   0.8011
  -1.750  -0.1817   0.02356   0.01358  -0.0038   0.9097   0.8091
  -1.500  -0.1465   0.02344   0.01332  -0.0056   0.9021   0.8176
  -1.250  -0.1170   0.02337   0.01315  -0.0063   0.8926   0.8260
  -1.000  -0.0856   0.02330   0.01300  -0.0074   0.8844   0.8343
  -0.750  -0.0554   0.02323   0.01285  -0.0083   0.8760   0.8436
  -0.500  -0.0253   0.02322   0.01280  -0.0090   0.8674   0.8516
  -0.250   0.0053   0.02316   0.01270  -0.0099   0.8599   0.8613
   0.000   0.0343   0.02319   0.01271  -0.0105   0.8511   0.8700
   0.250   0.0677   0.02318   0.01268  -0.0118   0.8444   0.8791
   0.500   0.0925   0.02324   0.01275  -0.0118   0.8353   0.8903
   0.750   0.1312   0.02325   0.01279  -0.0140   0.8292   0.8981
   1.000   0.1602   0.02336   0.01294  -0.0149   0.8207   0.9089
   1.250   0.1957   0.02340   0.01303  -0.0167   0.8143   0.9189
   1.500   0.2312   0.02354   0.01324  -0.0188   0.8065   0.9284
   1.750   0.2687   0.02362   0.01340  -0.0211   0.7998   0.9384
   2.000   0.3044   0.02377   0.01368  -0.0233   0.7924   0.9493
   2.250   0.3475   0.02387   0.01391  -0.0268   0.7852   0.9576
   2.500   0.3881   0.02401   0.01422  -0.0299   0.7777   0.9673
   2.750   0.4285   0.02409   0.01448  -0.0328   0.7693   0.9775
   3.000   0.4674   0.02424   0.01482  -0.0357   0.7598   0.9888
   3.250   0.5087   0.02423   0.01504  -0.0384   0.7518   1.0000
   3.500   0.5162   0.02462   0.01554  -0.0357   0.7402   1.0000
   3.750   0.5270   0.02489   0.01593  -0.0332   0.7290   1.0000
   4.000   0.5426   0.02496   0.01612  -0.0309   0.7171   1.0000
   4.250   0.5576   0.02485   0.01613  -0.0281   0.7004   1.0000
   4.500   0.5805   0.02392   0.01532  -0.0248   0.6754   1.0000
   4.750   0.5951   0.02301   0.01445  -0.0203   0.6380   1.0000
   5.000   0.6100   0.02214   0.01354  -0.0160   0.5904   1.0000
   5.250   0.6240   0.02175   0.01312  -0.0123   0.5323   1.0000
   5.500   0.6369   0.02172   0.01291  -0.0088   0.4302   1.0000
   5.750   0.6376   0.02324   0.01299  -0.0044   0.2390   1.0000
   6.000   0.6397   0.02543   0.01443  -0.0019   0.1568   1.0000
   6.250   0.6475   0.02721   0.01585   0.0000   0.1243   1.0000
   6.500   0.6591   0.02870   0.01722   0.0017   0.1085   1.0000
   6.750   0.6730   0.03009   0.01857   0.0032   0.0966   1.0000
   7.000   0.6904   0.03136   0.01993   0.0044   0.0868   1.0000
   7.250   0.7113   0.03280   0.02133   0.0054   0.0808   1.0000
   7.500   0.7379   0.03410   0.02282   0.0059   0.0737   1.0000
   7.750   0.7661   0.03574   0.02436   0.0059   0.0683   1.0000
   8.000   0.7983   0.03760   0.02655   0.0059   0.0647   1.0000
   8.250   0.8241   0.03949   0.02864   0.0062   0.0608   1.0000
   8.500   0.8473   0.04156   0.03073   0.0063   0.0575   1.0000
   8.750   0.8691   0.04419   0.03367   0.0068   0.0557   1.0000
   9.000   0.8864   0.04705   0.03699   0.0077   0.0546   1.0000
   9.250   0.8991   0.05011   0.04050   0.0088   0.0536   1.0000
   9.500   0.9068   0.05323   0.04404   0.0100   0.0526   1.0000
   9.750   0.9100   0.05637   0.04755   0.0114   0.0513   1.0000
  10.000   0.9098   0.05948   0.05097   0.0128   0.0502   1.0000
  10.250   0.9060   0.06270   0.05446   0.0141   0.0494   1.0000
  10.500   0.8964   0.06593   0.05792   0.0156   0.0490   1.0000
  10.750   0.8822   0.06953   0.06174   0.0165   0.0488   1.0000
  11.000   0.8634   0.07378   0.06620   0.0164   0.0488   1.0000
  11.250   0.8386   0.07910   0.07173   0.0147   0.0493   1.0000
  11.500   0.8108   0.08570   0.07849   0.0114   0.0499   1.0000
  11.750   0.7815   0.09392   0.08682   0.0061   0.0509   1.0000
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