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NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 200,000
Max Cl/Cd: 59.25 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a210-il-200000-n5.txt
Download as CSV file: xf-naca64a210-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5863   0.08287   0.07933  -0.0283   1.0000   0.0155
  -9.750  -0.5947   0.07468   0.07118  -0.0349   1.0000   0.0154
  -9.500  -0.6083   0.06709   0.06354  -0.0419   1.0000   0.0151
  -9.250  -0.6251   0.06154   0.05789  -0.0455   1.0000   0.0150
  -9.000  -0.6392   0.05640   0.05258  -0.0465   1.0000   0.0150
  -8.750  -0.6491   0.05122   0.04716  -0.0465   1.0000   0.0150
  -8.500  -0.6559   0.04631   0.04196  -0.0453   1.0000   0.0151
  -8.250  -0.6604   0.04177   0.03706  -0.0432   1.0000   0.0151
  -8.000  -0.6619   0.03774   0.03261  -0.0405   1.0000   0.0153
  -7.750  -0.6592   0.03440   0.02881  -0.0377   1.0000   0.0155
  -7.500  -0.6549   0.03120   0.02522  -0.0349   1.0000   0.0159
  -7.250  -0.6456   0.02898   0.02275  -0.0327   1.0000   0.0163
  -7.000  -0.6196   0.02770   0.02132  -0.0337   0.9971   0.0174
  -6.750  -0.5891   0.02625   0.01963  -0.0352   0.9934   0.0188
  -6.500  -0.5595   0.02407   0.01706  -0.0361   0.9893   0.0198
  -6.250  -0.5278   0.02213   0.01475  -0.0373   0.9861   0.0207
  -6.000  -0.4972   0.02068   0.01303  -0.0382   0.9818   0.0215
  -5.750  -0.4660   0.01921   0.01139  -0.0393   0.9781   0.0232
  -5.500  -0.4329   0.01810   0.01023  -0.0409   0.9751   0.0247
  -5.250  -0.4036   0.01715   0.00918  -0.0415   0.9695   0.0259
  -5.000  -0.3717   0.01626   0.00821  -0.0426   0.9652   0.0275
  -4.750  -0.3419   0.01550   0.00737  -0.0433   0.9598   0.0292
  -4.500  -0.3119   0.01483   0.00663  -0.0440   0.9540   0.0319
  -4.250  -0.2805   0.01415   0.00591  -0.0451   0.9494   0.0363
  -4.000  -0.2529   0.01367   0.00535  -0.0452   0.9418   0.0407
  -3.750  -0.2220   0.01312   0.00478  -0.0460   0.9366   0.0495
  -3.500  -0.1949   0.01268   0.00437  -0.0461   0.9288   0.0685
  -3.250  -0.1668   0.01198   0.00394  -0.0465   0.9227   0.1312
  -3.000  -0.1452   0.01079   0.00353  -0.0462   0.9140   0.3216
  -2.750  -0.1220   0.00992   0.00343  -0.0456   0.9074   0.5198
  -2.500  -0.0974   0.00970   0.00339  -0.0448   0.8987   0.5881
  -2.250  -0.0706   0.00955   0.00332  -0.0443   0.8921   0.6377
  -2.000  -0.0465   0.00945   0.00337  -0.0431   0.8832   0.6912
  -1.750  -0.0211   0.00939   0.00338  -0.0422   0.8759   0.7289
  -1.500   0.0057   0.00933   0.00328  -0.0418   0.8675   0.7448
  -1.250   0.0328   0.00927   0.00319  -0.0415   0.8594   0.7564
  -1.000   0.0602   0.00921   0.00310  -0.0413   0.8514   0.7670
  -0.750   0.0871   0.00917   0.00303  -0.0410   0.8425   0.7781
  -0.500   0.1146   0.00912   0.00294  -0.0408   0.8349   0.7894
  -0.250   0.1412   0.00907   0.00291  -0.0404   0.8252   0.8006
   0.000   0.1681   0.00903   0.00287  -0.0401   0.8166   0.8125
   0.250   0.1951   0.00899   0.00285  -0.0397   0.8080   0.8250
   0.500   0.2220   0.00896   0.00285  -0.0394   0.7986   0.8387
   0.750   0.2494   0.00894   0.00285  -0.0391   0.7902   0.8538
   1.000   0.2773   0.00893   0.00289  -0.0389   0.7811   0.8704
   1.250   0.3063   0.00894   0.00293  -0.0390   0.7722   0.8890
   1.500   0.3374   0.00896   0.00297  -0.0395   0.7639   0.9086
   1.750   0.3708   0.00899   0.00305  -0.0407   0.7544   0.9288
   2.000   0.4054   0.00903   0.00314  -0.0421   0.7455   0.9493
   2.250   0.4412   0.00908   0.00321  -0.0438   0.7355   0.9680
   2.500   0.4766   0.00913   0.00328  -0.0454   0.7215   0.9860
   2.750   0.5106   0.00919   0.00331  -0.0467   0.6954   1.0000
   3.000   0.5324   0.00931   0.00328  -0.0453   0.6558   1.0000
   3.250   0.5544   0.00950   0.00331  -0.0440   0.6134   1.0000
   3.500   0.5766   0.00975   0.00343  -0.0428   0.5698   1.0000
   3.750   0.5978   0.01009   0.00356  -0.0415   0.5115   1.0000
   4.000   0.6143   0.01083   0.00378  -0.0395   0.3948   1.0000
   4.250   0.6260   0.01225   0.00436  -0.0372   0.2300   1.0000
   4.500   0.6414   0.01350   0.00499  -0.0357   0.1134   1.0000
   4.750   0.6614   0.01432   0.00557  -0.0346   0.0672   1.0000
   5.000   0.6833   0.01494   0.00612  -0.0338   0.0494   1.0000
   5.250   0.7052   0.01558   0.00673  -0.0329   0.0393   1.0000
   5.500   0.7277   0.01613   0.00733  -0.0322   0.0333   1.0000
   5.750   0.7480   0.01697   0.00818  -0.0311   0.0295   1.0000
   6.000   0.7697   0.01765   0.00898  -0.0301   0.0276   1.0000
   6.250   0.7906   0.01843   0.00985  -0.0291   0.0260   1.0000
   6.500   0.8112   0.01928   0.01077  -0.0280   0.0246   1.0000
   6.750   0.8317   0.02021   0.01175  -0.0270   0.0235   1.0000
   7.000   0.8520   0.02124   0.01283  -0.0260   0.0225   1.0000
   7.250   0.8708   0.02284   0.01448  -0.0248   0.0212   1.0000
   7.500   0.8932   0.02376   0.01554  -0.0241   0.0203   1.0000
   7.750   0.9151   0.02504   0.01697  -0.0233   0.0197   1.0000
   8.000   0.9370   0.02652   0.01863  -0.0224   0.0190   1.0000
   8.250   0.9583   0.02819   0.02052  -0.0216   0.0184   1.0000
   8.500   0.9785   0.03005   0.02262  -0.0206   0.0179   1.0000
   8.750   0.9971   0.03169   0.02452  -0.0195   0.0171   1.0000
   9.000   1.0144   0.03301   0.02601  -0.0185   0.0162   1.0000
   9.250   1.0303   0.03441   0.02753  -0.0174   0.0155   1.0000
   9.500   1.0422   0.03697   0.03032  -0.0160   0.0150   1.0000
   9.750   1.0483   0.04035   0.03408  -0.0138   0.0147   1.0000
  10.000   1.0520   0.04330   0.03746  -0.0115   0.0145   1.0000
  10.250   1.0499   0.04668   0.04126  -0.0088   0.0143   1.0000
  10.500   1.0408   0.05018   0.04511  -0.0056   0.0141   1.0000
  10.750   1.0266   0.05379   0.04903  -0.0026   0.0140   1.0000
  11.000   1.0092   0.05775   0.05327  -0.0005   0.0139   1.0000
  11.250   0.9898   0.06219   0.05796   0.0004   0.0139   1.0000
  11.500   0.9690   0.06729   0.06328  -0.0002   0.0139   1.0000
  11.750   0.9471   0.07319   0.06937  -0.0023   0.0139   1.0000
  12.000   0.9247   0.08008   0.07642  -0.0061   0.0140   1.0000
  12.250   0.9020   0.08827   0.08474  -0.0115   0.0142   1.0000
  12.500   0.8794   0.09825   0.09482  -0.0185   0.0144   1.0000
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