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NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 (n64212-il)
Reynolds number: 200,000
Max Cl/Cd: 65.15 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212-il-200000.txt
Download as CSV file: xf-n64212-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4471   0.08982   0.08646  -0.0285   1.0000   0.0714
 -10.250  -0.4669   0.08213   0.07881  -0.0336   1.0000   0.0742
 -10.000  -0.5044   0.07142   0.06811  -0.0421   1.0000   0.0749
  -9.750  -0.5352   0.06431   0.06095  -0.0466   1.0000   0.0749
  -9.500  -0.5630   0.05902   0.05559  -0.0489   1.0000   0.0748
  -9.250  -0.5940   0.05532   0.05180  -0.0487   1.0000   0.0750
  -9.000  -0.6282   0.05294   0.04912  -0.0470   1.0000   0.0759
  -7.750  -0.6953   0.03828   0.03269  -0.0352   1.0000   0.0534
  -7.500  -0.6960   0.03276   0.02656  -0.0307   1.0000   0.0433
  -7.250  -0.6891   0.03113   0.02478  -0.0281   1.0000   0.0439
  -7.000  -0.6641   0.02852   0.02180  -0.0285   0.9970   0.0441
  -6.750  -0.6280   0.02561   0.01844  -0.0305   0.9924   0.0436
  -6.500  -0.5914   0.02358   0.01619  -0.0325   0.9875   0.0444
  -6.250  -0.5521   0.02202   0.01447  -0.0351   0.9837   0.0461
  -6.000  -0.5159   0.02089   0.01320  -0.0370   0.9775   0.0492
  -5.750  -0.4764   0.01972   0.01188  -0.0394   0.9731   0.0511
  -5.500  -0.4393   0.01786   0.01006  -0.0416   0.9693   0.0545
  -5.250  -0.4038   0.01702   0.00923  -0.0436   0.9625   0.0600
  -5.000  -0.3661   0.01588   0.00810  -0.0460   0.9577   0.0661
  -4.750  -0.3337   0.01513   0.00733  -0.0473   0.9495   0.0753
  -4.500  -0.3000   0.01412   0.00640  -0.0490   0.9429   0.0943
  -4.250  -0.2811   0.01193   0.00535  -0.0490   0.9318   0.3009
  -4.000  -0.2594   0.01100   0.00537  -0.0482   0.9227   0.5449
  -3.750  -0.2317   0.01101   0.00540  -0.0477   0.9140   0.5918
  -3.500  -0.2056   0.01108   0.00545  -0.0470   0.9045   0.6204
  -3.250  -0.1780   0.01114   0.00544  -0.0464   0.8969   0.6430
  -3.000  -0.1535   0.01125   0.00555  -0.0453   0.8868   0.6627
  -2.750  -0.1286   0.01148   0.00576  -0.0440   0.8788   0.6888
  -2.500  -0.1056   0.01177   0.00613  -0.0419   0.8697   0.7115
  -2.250  -0.0807   0.01189   0.00623  -0.0408   0.8611   0.7255
  -2.000  -0.0538   0.01184   0.00607  -0.0405   0.8530   0.7348
  -1.750  -0.0280   0.01184   0.00605  -0.0398   0.8442   0.7414
  -1.500  -0.0008   0.01180   0.00592  -0.0396   0.8370   0.7504
  -1.250   0.0252   0.01180   0.00591  -0.0390   0.8283   0.7568
  -1.000   0.0529   0.01175   0.00576  -0.0390   0.8214   0.7652
  -0.750   0.0788   0.01174   0.00578  -0.0384   0.8126   0.7711
  -0.500   0.1065   0.01171   0.00567  -0.0383   0.8059   0.7795
  -0.250   0.1327   0.01172   0.00571  -0.0379   0.7977   0.7857
   0.000   0.1602   0.01171   0.00565  -0.0378   0.7913   0.7943
   0.250   0.1861   0.01174   0.00571  -0.0374   0.7835   0.8013
   0.500   0.2136   0.01174   0.00568  -0.0372   0.7767   0.8105
   0.750   0.2394   0.01178   0.00576  -0.0367   0.7697   0.8174
   1.000   0.2665   0.01180   0.00579  -0.0366   0.7629   0.8267
   1.250   0.2922   0.01185   0.00586  -0.0359   0.7570   0.8346
   1.500   0.3181   0.01189   0.00595  -0.0355   0.7495   0.8440
   1.750   0.3444   0.01193   0.00599  -0.0350   0.7443   0.8534
   2.000   0.3689   0.01198   0.00614  -0.0343   0.7361   0.8623
   2.250   0.3950   0.01199   0.00615  -0.0337   0.7297   0.8726
   2.500   0.4186   0.01204   0.00630  -0.0327   0.7217   0.8828
   2.750   0.4431   0.01205   0.00635  -0.0317   0.7155   0.8932
   3.000   0.4667   0.01209   0.00647  -0.0308   0.7074   0.9048
   3.250   0.4915   0.01198   0.00635  -0.0296   0.6984   0.9168
   3.500   0.5146   0.01175   0.00613  -0.0280   0.6833   0.9295
   3.750   0.5385   0.01147   0.00589  -0.0266   0.6632   0.9427
   4.000   0.5675   0.01119   0.00561  -0.0263   0.6413   0.9553
   4.250   0.6024   0.01106   0.00549  -0.0275   0.6210   0.9664
   4.500   0.6405   0.01097   0.00548  -0.0295   0.5968   0.9769
   4.750   0.6803   0.01094   0.00544  -0.0319   0.5639   0.9872
   5.000   0.7193   0.01104   0.00544  -0.0344   0.4982   0.9993
   5.250   0.7207   0.01174   0.00554  -0.0301   0.3660   1.0000
   5.500   0.7158   0.01424   0.00666  -0.0263   0.1410   1.0000
   5.750   0.7295   0.01576   0.00775  -0.0249   0.0845   1.0000
   6.000   0.7488   0.01674   0.00865  -0.0240   0.0701   1.0000
   6.250   0.7680   0.01774   0.00965  -0.0230   0.0624   1.0000
   6.500   0.7860   0.01886   0.01071  -0.0219   0.0561   1.0000
   6.750   0.8064   0.01985   0.01174  -0.0210   0.0519   1.0000
   7.000   0.8276   0.02083   0.01273  -0.0202   0.0484   1.0000
   7.250   0.8486   0.02219   0.01403  -0.0195   0.0456   1.0000
   7.500   0.8736   0.02413   0.01599  -0.0192   0.0437   1.0000
   7.750   0.8987   0.02527   0.01726  -0.0188   0.0421   1.0000
   8.000   0.9231   0.02649   0.01860  -0.0184   0.0399   1.0000
   8.250   0.9485   0.02811   0.02033  -0.0182   0.0386   1.0000
   8.500   0.9731   0.02996   0.02234  -0.0179   0.0378   1.0000
   8.750   0.9967   0.03213   0.02470  -0.0175   0.0372   1.0000
   9.000   1.0186   0.03476   0.02761  -0.0168   0.0372   1.0000
   9.250   1.0353   0.03783   0.03108  -0.0155   0.0375   1.0000
   9.500   1.0524   0.04030   0.03371  -0.0147   0.0367   1.0000
   9.750   1.0654   0.04337   0.03699  -0.0137   0.0361   1.0000
  10.000   1.0473   0.05127   0.04597  -0.0088   0.0418   1.0000
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