Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 (n64212-il)
Reynolds number: 500,000
Max Cl/Cd: 80.25 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212-il-500000.txt
Download as CSV file: xf-n64212-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4586   0.10346   0.10127  -0.0211   1.0000   0.0288
 -11.500  -0.4642   0.09767   0.09550  -0.0237   1.0000   0.0295
 -10.250  -0.7956   0.04463   0.04123  -0.0484   1.0000   0.0207
 -10.000  -0.7957   0.04093   0.03730  -0.0467   1.0000   0.0193
  -9.750  -0.8015   0.03680   0.03285  -0.0446   1.0000   0.0191
  -9.500  -0.8003   0.03332   0.02902  -0.0426   1.0000   0.0191
  -9.250  -0.7939   0.03043   0.02578  -0.0407   1.0000   0.0193
  -9.000  -0.7837   0.02834   0.02341  -0.0387   1.0000   0.0196
  -8.500  -0.7611   0.02370   0.01829  -0.0353   0.9981   0.0207
  -8.250  -0.7282   0.02224   0.01673  -0.0374   0.9931   0.0214
  -8.000  -0.6951   0.02086   0.01522  -0.0392   0.9878   0.0220
  -7.750  -0.6602   0.01954   0.01378  -0.0413   0.9839   0.0227
  -7.500  -0.6274   0.01837   0.01247  -0.0427   0.9770   0.0235
  -7.250  -0.5924   0.01746   0.01145  -0.0446   0.9712   0.0246
  -7.000  -0.5598   0.01703   0.01090  -0.0458   0.9619   0.0254
  -6.750  -0.5338   0.01511   0.00893  -0.0461   0.9516   0.0267
  -6.500  -0.5079   0.01441   0.00819  -0.0460   0.9402   0.0278
  -6.250  -0.4844   0.01387   0.00759  -0.0453   0.9278   0.0290
  -6.000  -0.4612   0.01339   0.00704  -0.0445   0.9158   0.0305
  -5.750  -0.4370   0.01304   0.00662  -0.0439   0.9050   0.0319
  -5.500  -0.4155   0.01223   0.00572  -0.0429   0.8946   0.0344
  -5.250  -0.3914   0.01179   0.00524  -0.0424   0.8843   0.0371
  -5.000  -0.3661   0.01145   0.00484  -0.0419   0.8745   0.0398
  -4.750  -0.3416   0.01097   0.00428  -0.0414   0.8656   0.0442
  -4.500  -0.3157   0.01066   0.00393  -0.0411   0.8560   0.0501
  -4.250  -0.2899   0.01027   0.00354  -0.0409   0.8475   0.0610
  -4.000  -0.2650   0.00967   0.00314  -0.0406   0.8385   0.1073
  -3.750  -0.2430   0.00841   0.00261  -0.0405   0.8296   0.2865
  -3.500  -0.2201   0.00745   0.00232  -0.0403   0.8212   0.4746
  -3.250  -0.1931   0.00726   0.00226  -0.0402   0.8125   0.5262
  -3.000  -0.1656   0.00720   0.00219  -0.0401   0.8050   0.5552
  -2.750  -0.1376   0.00714   0.00214  -0.0401   0.7964   0.5765
  -2.500  -0.1097   0.00713   0.00208  -0.0400   0.7891   0.5933
  -2.250  -0.0815   0.00710   0.00205  -0.0401   0.7805   0.6082
  -2.000  -0.0540   0.00711   0.00206  -0.0399   0.7731   0.6315
  -1.750  -0.0263   0.00715   0.00212  -0.0397   0.7645   0.6553
  -1.500   0.0016   0.00716   0.00210  -0.0396   0.7573   0.6662
  -1.250   0.0302   0.00715   0.00206  -0.0398   0.7492   0.6745
  -1.000   0.0583   0.00716   0.00205  -0.0398   0.7423   0.6823
  -0.750   0.0869   0.00715   0.00202  -0.0399   0.7345   0.6896
  -0.500   0.1151   0.00716   0.00200  -0.0399   0.7278   0.6963
  -0.250   0.1438   0.00716   0.00199  -0.0401   0.7200   0.7039
   0.000   0.1719   0.00718   0.00199  -0.0401   0.7133   0.7103
   0.250   0.2006   0.00719   0.00201  -0.0403   0.7058   0.7181
   0.500   0.2287   0.00720   0.00203  -0.0404   0.6995   0.7250
   0.750   0.2574   0.00723   0.00207  -0.0405   0.6927   0.7334
   1.000   0.2855   0.00725   0.00211  -0.0406   0.6861   0.7407
   1.250   0.3140   0.00730   0.00216  -0.0407   0.6796   0.7491
   1.500   0.3420   0.00730   0.00221  -0.0407   0.6721   0.7564
   2.000   0.3982   0.00737   0.00234  -0.0407   0.6572   0.7728
   2.250   0.4262   0.00743   0.00240  -0.0408   0.6489   0.7817
   2.500   0.4534   0.00744   0.00244  -0.0405   0.6357   0.7902
   2.750   0.4803   0.00744   0.00245  -0.0402   0.6161   0.7989
   3.000   0.5072   0.00749   0.00248  -0.0399   0.5973   0.8079
   3.250   0.5341   0.00754   0.00255  -0.0397   0.5813   0.8163
   3.500   0.5616   0.00762   0.00266  -0.0396   0.5679   0.8259
   3.750   0.5879   0.00769   0.00276  -0.0392   0.5505   0.8346
   4.000   0.6142   0.00780   0.00287  -0.0389   0.5278   0.8442
   4.250   0.6396   0.00797   0.00300  -0.0384   0.4939   0.8543
   4.500   0.6616   0.00839   0.00319  -0.0374   0.4174   0.8641
   4.750   0.6757   0.00974   0.00378  -0.0356   0.2537   0.8753
   5.000   0.6915   0.01094   0.00442  -0.0340   0.1338   0.8875
   5.250   0.7092   0.01181   0.00498  -0.0325   0.0690   0.9005
   5.500   0.7292   0.01229   0.00541  -0.0311   0.0514   0.9141
   5.750   0.7485   0.01274   0.00587  -0.0295   0.0434   0.9299
   6.000   0.7677   0.01302   0.00623  -0.0278   0.0391   0.9494
   6.250   0.7929   0.01369   0.00695  -0.0277   0.0345   0.9760
   6.500   0.8223   0.01418   0.00747  -0.0285   0.0315   1.0000
   6.750   0.8460   0.01482   0.00810  -0.0283   0.0290   1.0000
   7.000   0.8660   0.01578   0.00910  -0.0274   0.0270   1.0000
   7.250   0.8890   0.01639   0.00976  -0.0269   0.0258   1.0000
   7.500   0.9110   0.01706   0.01047  -0.0263   0.0246   1.0000
   7.750   0.9322   0.01779   0.01122  -0.0256   0.0236   1.0000
   8.000   0.9524   0.01860   0.01205  -0.0248   0.0227   1.0000
   8.250   0.9698   0.01995   0.01343  -0.0236   0.0219   1.0000
   8.500   0.9892   0.02148   0.01503  -0.0226   0.0213   1.0000
   8.750   1.0111   0.02218   0.01582  -0.0220   0.0207   1.0000
   9.000   1.0323   0.02302   0.01676  -0.0212   0.0200   1.0000
   9.250   1.0532   0.02419   0.01802  -0.0205   0.0195   1.0000
   9.500   1.0738   0.02541   0.01935  -0.0198   0.0190   1.0000
   9.750   1.0938   0.02665   0.02068  -0.0191   0.0186   1.0000
  10.000   1.1126   0.02799   0.02213  -0.0182   0.0182   1.0000
  10.250   1.1303   0.02954   0.02382  -0.0173   0.0179   1.0000
  10.500   1.1463   0.03102   0.02540  -0.0163   0.0176   1.0000
  10.750   1.1609   0.03290   0.02741  -0.0152   0.0172   1.0000
  11.000   1.1724   0.03556   0.03027  -0.0140   0.0170   1.0000
  11.250   1.1685   0.03996   0.03504  -0.0113   0.0166   1.0000
  11.500   1.1649   0.04162   0.03691  -0.0081   0.0165   1.0000
  11.750   1.1598   0.04359   0.03910  -0.0053   0.0163   1.0000
  12.000   1.1505   0.04633   0.04209  -0.0029   0.0162   1.0000
  12.250   1.1384   0.04954   0.04553  -0.0011   0.0162   1.0000
  12.500   1.1223   0.05353   0.04975   0.0001   0.0163   1.0000
  12.750   1.1040   0.05786   0.05430   0.0006   0.0163   1.0000
  13.000   1.0840   0.06274   0.05939   0.0001   0.0163   1.0000
  13.250   1.0630   0.06822   0.06506  -0.0012   0.0164   1.0000
  13.500   1.0396   0.07463   0.07164  -0.0036   0.0165   1.0000
  13.750   0.9831   0.08774   0.08523  -0.0106   0.0177   1.0000
  14.000   0.9797   0.09197   0.08950  -0.0133   0.0175   1.0000
  14.250   0.9801   0.09561   0.09314  -0.0155   0.0172   1.0000
  14.500   0.6658   0.14927   0.14742  -0.0455   0.0275   1.0000
  14.750   0.6621   0.15478   0.15293  -0.0487   0.0274   1.0000
<< Back to NACA 64(1)-212 (n64212-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(1)-212 (n64212-il)