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NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-208 (naca64208-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.07 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64208-il-1000000-n5.txt
Download as CSV file: xf-naca64208-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-208                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5869   0.10223   0.10059  -0.0053   1.0000   0.0031
 -10.250  -0.5829   0.09888   0.09725  -0.0071   1.0000   0.0033
  -9.250  -0.8249   0.02163   0.01811  -0.0380   1.0000   0.0030
  -9.000  -0.8058   0.01968   0.01589  -0.0375   1.0000   0.0032
  -8.750  -0.7839   0.01855   0.01461  -0.0370   1.0000   0.0033
  -8.500  -0.7609   0.01770   0.01364  -0.0367   1.0000   0.0035
  -8.250  -0.7384   0.01669   0.01246  -0.0362   1.0000   0.0037
  -8.000  -0.7155   0.01581   0.01144  -0.0357   1.0000   0.0040
  -7.750  -0.6929   0.01487   0.01035  -0.0351   1.0000   0.0042
  -7.500  -0.6678   0.01399   0.00932  -0.0350   0.9988   0.0045
  -7.250  -0.6369   0.01321   0.00842  -0.0361   0.9936   0.0047
  -7.000  -0.6055   0.01255   0.00764  -0.0372   0.9881   0.0049
  -6.750  -0.5746   0.01164   0.00662  -0.0384   0.9814   0.0055
  -6.500  -0.5421   0.01127   0.00623  -0.0397   0.9742   0.0060
  -6.250  -0.5099   0.01103   0.00595  -0.0409   0.9652   0.0067
  -6.000  -0.4794   0.01075   0.00562  -0.0417   0.9539   0.0075
  -5.750  -0.4512   0.01042   0.00521  -0.0419   0.9412   0.0079
  -5.500  -0.4243   0.01016   0.00487  -0.0418   0.9279   0.0082
  -5.250  -0.3992   0.00945   0.00402  -0.0414   0.9144   0.0094
  -5.000  -0.3729   0.00920   0.00370  -0.0412   0.9019   0.0102
  -4.750  -0.3463   0.00901   0.00346  -0.0410   0.8899   0.0110
  -4.500  -0.3196   0.00881   0.00320  -0.0409   0.8783   0.0119
  -4.250  -0.2929   0.00856   0.00287  -0.0407   0.8669   0.0124
  -3.750  -0.2387   0.00818   0.00234  -0.0405   0.8449   0.0133
  -3.500  -0.2115   0.00785   0.00191  -0.0404   0.8345   0.0160
  -3.250  -0.1841   0.00769   0.00172  -0.0404   0.8242   0.0188
  -2.750  -0.1289   0.00745   0.00139  -0.0404   0.8042   0.0256
  -2.500  -0.1012   0.00733   0.00125  -0.0404   0.7944   0.0316
  -2.250  -0.0736   0.00723   0.00113  -0.0404   0.7841   0.0396
  -2.000  -0.0459   0.00705   0.00101  -0.0405   0.7739   0.0675
  -1.750  -0.0187   0.00659   0.00087  -0.0407   0.7645   0.1697
  -1.500   0.0085   0.00611   0.00072  -0.0409   0.7551   0.2900
  -1.250   0.0355   0.00561   0.00061  -0.0412   0.7451   0.4227
  -1.000   0.0629   0.00532   0.00057  -0.0413   0.7351   0.5147
  -0.750   0.0901   0.00504   0.00057  -0.0414   0.7255   0.6087
  -0.250   0.1456   0.00489   0.00059  -0.0414   0.7072   0.6842
   0.000   0.1736   0.00489   0.00060  -0.0414   0.6982   0.6973
   0.250   0.2016   0.00491   0.00061  -0.0415   0.6872   0.7080
   0.500   0.2294   0.00496   0.00062  -0.0415   0.6694   0.7175
   0.750   0.2567   0.00505   0.00064  -0.0414   0.6425   0.7277
   1.000   0.2841   0.00514   0.00068  -0.0413   0.6161   0.7382
   1.250   0.3110   0.00530   0.00073  -0.0412   0.5755   0.7487
   1.500   0.3373   0.00557   0.00080  -0.0410   0.5138   0.7591
   1.750   0.3638   0.00585   0.00089  -0.0408   0.4548   0.7695
   2.000   0.3881   0.00649   0.00110  -0.0405   0.3292   0.7801
   2.250   0.4118   0.00731   0.00140  -0.0402   0.1830   0.7912
   2.500   0.4371   0.00785   0.00164  -0.0400   0.0946   0.8025
   3.000   0.4902   0.00838   0.00200  -0.0397   0.0370   0.8246
   3.250   0.5170   0.00855   0.00220  -0.0396   0.0287   0.8359
   3.500   0.5439   0.00869   0.00238  -0.0395   0.0252   0.8477
   3.750   0.5704   0.00888   0.00258  -0.0393   0.0201   0.8598
   4.000   0.5967   0.00908   0.00283  -0.0390   0.0164   0.8727
   4.250   0.6227   0.00926   0.00307  -0.0386   0.0152   0.8862
   4.500   0.6482   0.00946   0.00335  -0.0382   0.0140   0.9010
   4.750   0.6731   0.00968   0.00363  -0.0376   0.0129   0.9170
   5.000   0.6972   0.00995   0.00395  -0.0369   0.0119   0.9351
   5.250   0.7206   0.01039   0.00452  -0.0360   0.0105   0.9585
   5.500   0.7500   0.01081   0.00501  -0.0365   0.0100   1.0000
   5.750   0.7762   0.01118   0.00545  -0.0364   0.0098   1.0000
   6.000   0.8024   0.01155   0.00585  -0.0363   0.0094   1.0000
   6.250   0.8285   0.01190   0.00624  -0.0361   0.0088   1.0000
   6.500   0.8544   0.01227   0.00664  -0.0360   0.0082   1.0000
   6.750   0.8801   0.01268   0.00709  -0.0358   0.0077   1.0000
   7.000   0.9058   0.01305   0.00749  -0.0356   0.0073   1.0000
   7.250   0.9309   0.01352   0.00798  -0.0354   0.0067   1.0000
   7.500   0.9536   0.01447   0.00906  -0.0348   0.0060   1.0000
   7.750   0.9796   0.01472   0.00935  -0.0347   0.0058   1.0000
   8.000   1.0048   0.01513   0.00981  -0.0345   0.0054   1.0000
   8.250   1.0295   0.01559   0.01032  -0.0342   0.0049   1.0000
   8.500   1.0539   0.01610   0.01089  -0.0339   0.0045   1.0000
   8.750   1.0786   0.01653   0.01135  -0.0337   0.0042   1.0000
   9.000   1.1028   0.01703   0.01189  -0.0334   0.0039   1.0000
   9.250   1.1237   0.01817   0.01317  -0.0326   0.0035   1.0000
   9.500   1.1460   0.01902   0.01416  -0.0320   0.0034   1.0000
   9.750   1.1678   0.01989   0.01517  -0.0315   0.0032   1.0000
  10.000   1.1887   0.02091   0.01633  -0.0308   0.0031   1.0000
  10.250   1.2087   0.02204   0.01762  -0.0300   0.0030   1.0000
  10.500   1.2279   0.02326   0.01900  -0.0292   0.0028   1.0000
  10.750   1.2465   0.02447   0.02037  -0.0283   0.0027   1.0000
  11.000   1.2640   0.02578   0.02184  -0.0274   0.0025   1.0000
  11.250   1.2802   0.02719   0.02342  -0.0264   0.0024   1.0000
  11.500   1.2946   0.02875   0.02516  -0.0252   0.0023   1.0000
  11.750   1.3079   0.03033   0.02690  -0.0239   0.0022   1.0000
  12.000   1.3157   0.03249   0.02929  -0.0222   0.0022   1.0000
  12.250   1.3190   0.03496   0.03201  -0.0202   0.0021   1.0000
  12.500   1.3122   0.03775   0.03504  -0.0171   0.0020   1.0000
  12.750   1.2969   0.04091   0.03844  -0.0136   0.0020   1.0000
  13.000   1.2714   0.04556   0.04336  -0.0112   0.0020   1.0000
  13.250   1.2382   0.05187   0.04995  -0.0108   0.0020   1.0000
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