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NACA 64(2)-215 (naca642215-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(2)-215 (naca642215-il)
Reynolds number: 200,000
Max Cl/Cd: 63.13 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca642215-il-200000.txt
Download as CSV file: xf-naca642215-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(2)-215                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6104   0.07197   0.06819  -0.0542   1.0000   0.0523
 -12.250  -0.6242   0.06575   0.06193  -0.0559   1.0000   0.0513
 -12.000  -0.6493   0.05922   0.05530  -0.0579   1.0000   0.0503
 -11.750  -0.6829   0.05277   0.04867  -0.0595   1.0000   0.0492
 -11.500  -0.8007   0.05551   0.05083  -0.0586   1.0000   0.0470
 -11.250  -0.8511   0.05109   0.04582  -0.0538   1.0000   0.0438
 -11.000  -0.8554   0.04773   0.04227  -0.0520   1.0000   0.0435
 -10.750  -0.8599   0.04501   0.03927  -0.0497   1.0000   0.0436
 -10.500  -0.8596   0.04234   0.03633  -0.0476   1.0000   0.0437
 -10.250  -0.8578   0.04011   0.03383  -0.0451   1.0000   0.0439
 -10.000  -0.8562   0.03805   0.03155  -0.0421   1.0000   0.0441
  -9.750  -0.8598   0.03649   0.02982  -0.0380   1.0000   0.0441
  -9.500  -0.8676   0.03542   0.02858  -0.0331   1.0000   0.0442
  -9.250  -0.8396   0.03274   0.02556  -0.0347   0.9951   0.0447
  -9.000  -0.8051   0.02966   0.02236  -0.0371   0.9908   0.0458
  -8.750  -0.7678   0.02813   0.02081  -0.0399   0.9856   0.0478
  -8.500  -0.7295   0.02664   0.01919  -0.0426   0.9810   0.0499
  -8.250  -0.6916   0.02516   0.01752  -0.0449   0.9756   0.0516
  -8.000  -0.6510   0.02363   0.01586  -0.0477   0.9719   0.0535
  -7.750  -0.6153   0.02217   0.01451  -0.0499   0.9660   0.0569
  -7.500  -0.5784   0.02118   0.01348  -0.0522   0.9594   0.0607
  -7.250  -0.5459   0.02003   0.01229  -0.0536   0.9514   0.0641
  -7.000  -0.5164   0.01901   0.01134  -0.0547   0.9426   0.0690
  -6.750  -0.4922   0.01840   0.01064  -0.0544   0.9310   0.0744
  -6.500  -0.4741   0.01751   0.00981  -0.0533   0.9194   0.0811
  -6.250  -0.4556   0.01677   0.00907  -0.0520   0.9091   0.0909
  -6.000  -0.4395   0.01602   0.00839  -0.0503   0.8973   0.1077
  -5.750  -0.4273   0.01483   0.00755  -0.0484   0.8864   0.1645
  -5.500  -0.4229   0.01285   0.00664  -0.0458   0.8767   0.3652
  -5.250  -0.4044   0.01251   0.00672  -0.0442   0.8665   0.4892
  -5.000  -0.3800   0.01256   0.00677  -0.0432   0.8589   0.5274
  -4.750  -0.3549   0.01267   0.00679  -0.0424   0.8499   0.5536
  -4.500  -0.3291   0.01279   0.00684  -0.0416   0.8432   0.5727
  -4.250  -0.3031   0.01291   0.00692  -0.0410   0.8345   0.5889
  -4.000  -0.2768   0.01306   0.00697  -0.0403   0.8284   0.6045
  -3.750  -0.2509   0.01327   0.00716  -0.0396   0.8197   0.6201
  -3.500  -0.2246   0.01350   0.00738  -0.0386   0.8132   0.6342
  -3.250  -0.1987   0.01378   0.00769  -0.0377   0.8054   0.6478
  -3.000  -0.1725   0.01402   0.00792  -0.0367   0.7985   0.6603
  -2.750  -0.1455   0.01407   0.00785  -0.0365   0.7923   0.6704
  -2.500  -0.1184   0.01406   0.00785  -0.0362   0.7849   0.6749
  -2.250  -0.0906   0.01401   0.00771  -0.0361   0.7794   0.6801
  -2.000  -0.0629   0.01394   0.00754  -0.0364   0.7724   0.6867
  -1.750  -0.0355   0.01391   0.00750  -0.0361   0.7660   0.6907
  -1.500  -0.0076   0.01389   0.00741  -0.0360   0.7611   0.6959
  -1.250   0.0201   0.01384   0.00732  -0.0363   0.7535   0.7022
  -1.000   0.0480   0.01378   0.00722  -0.0363   0.7480   0.7062
  -0.750   0.0759   0.01379   0.00720  -0.0363   0.7431   0.7107
  -0.500   0.1036   0.01379   0.00720  -0.0365   0.7366   0.7165
  -0.250   0.1320   0.01374   0.00710  -0.0367   0.7317   0.7217
   0.000   0.1600   0.01376   0.00711  -0.0367   0.7273   0.7260
   0.250   0.1873   0.01380   0.00719  -0.0368   0.7208   0.7316
   0.500   0.2158   0.01379   0.00714  -0.0371   0.7158   0.7380
   0.750   0.2437   0.01383   0.00718  -0.0369   0.7121   0.7428
   1.000   0.2708   0.01393   0.00735  -0.0371   0.7064   0.7489
   1.250   0.2989   0.01397   0.00739  -0.0373   0.7014   0.7552
   1.500   0.3265   0.01401   0.00745  -0.0372   0.6973   0.7604
   1.750   0.3543   0.01412   0.00759  -0.0373   0.6928   0.7674
   2.000   0.3810   0.01422   0.00777  -0.0373   0.6873   0.7737
   2.250   0.4083   0.01426   0.00785  -0.0371   0.6825   0.7803
   2.500   0.4371   0.01432   0.00789  -0.0372   0.6785   0.7881
   2.750   0.4619   0.01446   0.00818  -0.0368   0.6723   0.7943
   3.000   0.4899   0.01454   0.00830  -0.0369   0.6675   0.8026
   3.250   0.5170   0.01459   0.00838  -0.0366   0.6636   0.8089
   3.500   0.5427   0.01475   0.00866  -0.0364   0.6576   0.8172
   3.750   0.5688   0.01468   0.00865  -0.0358   0.6503   0.8245
   4.000   0.5949   0.01461   0.00862  -0.0351   0.6416   0.8334
   4.250   0.6211   0.01435   0.00835  -0.0342   0.6312   0.8412
   4.500   0.6456   0.01420   0.00828  -0.0333   0.6190   0.8509
   4.750   0.6693   0.01401   0.00816  -0.0320   0.6070   0.8589
   5.000   0.6944   0.01379   0.00794  -0.0311   0.5929   0.8690
   5.250   0.7167   0.01360   0.00779  -0.0295   0.5791   0.8780
   5.500   0.7396   0.01347   0.00771  -0.0282   0.5657   0.8884
   5.750   0.7612   0.01337   0.00769  -0.0267   0.5502   0.9003
   6.000   0.7806   0.01325   0.00764  -0.0247   0.5327   0.9120
   6.250   0.7991   0.01314   0.00765  -0.0227   0.5095   0.9254
   6.500   0.8178   0.01307   0.00760  -0.0207   0.4779   0.9407
   6.750   0.8359   0.01324   0.00759  -0.0190   0.4068   0.9586
   7.000   0.8464   0.01516   0.00851  -0.0181   0.2396   0.9819
   7.250   0.8493   0.01712   0.00979  -0.0165   0.1376   1.0000
   7.500   0.8543   0.01859   0.01093  -0.0144   0.1005   1.0000
   7.750   0.8628   0.01971   0.01194  -0.0125   0.0853   1.0000
   8.000   0.8700   0.02095   0.01308  -0.0105   0.0766   1.0000
   8.250   0.8832   0.02191   0.01406  -0.0092   0.0699   1.0000
   8.500   0.8910   0.02329   0.01536  -0.0075   0.0651   1.0000
   8.750   0.9051   0.02431   0.01644  -0.0063   0.0612   1.0000
   9.000   0.9176   0.02549   0.01758  -0.0052   0.0577   1.0000
   9.250   0.9313   0.02685   0.01890  -0.0040   0.0546   1.0000
   9.500   0.9481   0.02787   0.01998  -0.0032   0.0517   1.0000
   9.750   0.9657   0.02898   0.02109  -0.0024   0.0495   1.0000
  10.000   0.9936   0.03062   0.02258  -0.0023   0.0469   1.0000
  10.250   1.0137   0.03170   0.02381  -0.0017   0.0456   1.0000
  10.500   1.0350   0.03290   0.02512  -0.0012   0.0439   1.0000
  10.750   1.0545   0.03413   0.02642  -0.0007   0.0421   1.0000
  11.000   1.0775   0.03552   0.02781  -0.0006   0.0406   1.0000
  11.250   1.1233   0.03852   0.03083  -0.0029   0.0392   1.0000
  11.500   1.1351   0.04022   0.03278  -0.0015   0.0388   1.0000
  11.750   1.1460   0.04229   0.03513  -0.0002   0.0384   1.0000
  12.000   1.1549   0.04463   0.03774   0.0011   0.0380   1.0000
  12.250   1.1585   0.04715   0.04054   0.0027   0.0377   1.0000
  12.500   1.1585   0.04981   0.04346   0.0043   0.0373   1.0000
  12.750   1.1548   0.05257   0.04648   0.0058   0.0370   1.0000
  13.000   1.1478   0.05572   0.04988   0.0071   0.0368   1.0000
  13.250   1.1370   0.05916   0.05358   0.0081   0.0365   1.0000
  13.500   1.1226   0.06328   0.05796   0.0088   0.0368   1.0000
  13.750   1.1044   0.06784   0.06278   0.0089   0.0369   1.0000
  14.000   1.0846   0.07285   0.06803   0.0083   0.0372   1.0000
  14.250   1.0636   0.07830   0.07369   0.0071   0.0376   1.0000
  14.500   1.0401   0.08436   0.07996   0.0050   0.0378   1.0000
  14.750   1.0170   0.09089   0.08667   0.0024   0.0382   1.0000
  15.000   0.9947   0.09794   0.09386  -0.0009   0.0386   1.0000
  15.250   0.9752   0.10536   0.10139  -0.0044   0.0390   1.0000
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