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)-112 (naca641112-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-112 (naca641112-il)
Reynolds number: 500,000
Max Cl/Cd: 68.35 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca641112-il-500000.txt
Download as CSV file: xf-naca641112-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-112                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6425   0.11112   0.10881  -0.0088   1.0000   0.0268
 -12.250  -0.6421   0.10680   0.10449  -0.0108   1.0000   0.0271
 -12.000  -0.6429   0.10217   0.09987  -0.0131   1.0000   0.0274
 -11.750  -0.6467   0.09653   0.09425  -0.0162   1.0000   0.0278
 -11.000  -0.8340   0.05156   0.04840  -0.0403   1.0000   0.0198
 -10.750  -0.8549   0.04797   0.04464  -0.0385   1.0000   0.0196
 -10.500  -0.8716   0.04462   0.04109  -0.0357   1.0000   0.0194
 -10.250  -0.8819   0.04059   0.03677  -0.0335   1.0000   0.0191
 -10.000  -0.8860   0.03656   0.03238  -0.0313   1.0000   0.0190
  -9.750  -0.8831   0.03295   0.02841  -0.0294   1.0000   0.0190
  -9.500  -0.8734   0.03003   0.02514  -0.0279   1.0000   0.0192
  -9.250  -0.8591   0.02770   0.02253  -0.0266   1.0000   0.0195
  -9.000  -0.8414   0.02609   0.02067  -0.0256   1.0000   0.0199
  -8.750  -0.8232   0.02465   0.01897  -0.0246   1.0000   0.0205
  -8.500  -0.8045   0.02210   0.01628  -0.0238   1.0000   0.0212
  -8.250  -0.7839   0.02087   0.01499  -0.0231   1.0000   0.0217
  -8.000  -0.7638   0.01991   0.01398  -0.0222   1.0000   0.0222
  -7.750  -0.7458   0.01910   0.01312  -0.0209   0.9993   0.0228
  -7.500  -0.7112   0.01802   0.01197  -0.0228   0.9911   0.0237
  -7.000  -0.6406   0.01655   0.01032  -0.0267   0.9744   0.0258
  -6.750  -0.6112   0.01501   0.00872  -0.0277   0.9631   0.0271
  -6.500  -0.5840   0.01422   0.00789  -0.0281   0.9498   0.0284
  -6.250  -0.5603   0.01371   0.00732  -0.0275   0.9357   0.0298
  -6.000  -0.5380   0.01327   0.00681  -0.0265   0.9225   0.0315
  -5.750  -0.5150   0.01293   0.00639  -0.0256   0.9107   0.0329
  -5.500  -0.4944   0.01218   0.00557  -0.0244   0.8989   0.0362
  -5.250  -0.4704   0.01180   0.00515  -0.0238   0.8879   0.0393
  -5.000  -0.4457   0.01149   0.00475  -0.0232   0.8780   0.0425
  -4.750  -0.4219   0.01100   0.00424  -0.0225   0.8682   0.0495
  -4.500  -0.3967   0.01060   0.00384  -0.0222   0.8584   0.0610
  -4.250  -0.3731   0.00997   0.00341  -0.0217   0.8496   0.1095
  -4.000  -0.3524   0.00877   0.00287  -0.0212   0.8399   0.2633
  -3.750  -0.3317   0.00762   0.00249  -0.0207   0.8307   0.4589
  -3.500  -0.3058   0.00740   0.00238  -0.0204   0.8224   0.5163
  -3.250  -0.2784   0.00729   0.00231  -0.0203   0.8134   0.5482
  -3.000  -0.2510   0.00724   0.00223  -0.0201   0.8058   0.5685
  -2.750  -0.2231   0.00718   0.00217  -0.0201   0.7970   0.5859
  -2.500  -0.1953   0.00716   0.00212  -0.0200   0.7894   0.6009
  -2.250  -0.1676   0.00714   0.00211  -0.0199   0.7808   0.6210
  -2.000  -0.1402   0.00716   0.00214  -0.0197   0.7730   0.6446
  -1.750  -0.1124   0.00717   0.00214  -0.0196   0.7646   0.6595
  -1.500  -0.0842   0.00717   0.00210  -0.0196   0.7570   0.6679
  -1.250  -0.0559   0.00714   0.00206  -0.0197   0.7491   0.6755
  -1.000  -0.0275   0.00715   0.00203  -0.0197   0.7419   0.6836
  -0.750   0.0009   0.00713   0.00200  -0.0198   0.7342   0.6903
  -0.500   0.0293   0.00714   0.00199  -0.0199   0.7272   0.6973
  -0.250   0.0578   0.00713   0.00197  -0.0200   0.7194   0.7043
   0.000   0.0860   0.00714   0.00197  -0.0201   0.7126   0.7111
   0.250   0.1147   0.00715   0.00198  -0.0203   0.7052   0.7186
   0.500   0.1428   0.00717   0.00200  -0.0203   0.6991   0.7258
   0.750   0.1715   0.00718   0.00203  -0.0205   0.6919   0.7338
   1.000   0.1996   0.00720   0.00206  -0.0205   0.6855   0.7412
   1.250   0.2282   0.00723   0.00211  -0.0206   0.6781   0.7492
   1.500   0.2562   0.00725   0.00215  -0.0206   0.6707   0.7567
   1.750   0.2846   0.00727   0.00221  -0.0207   0.6628   0.7650
   2.000   0.3125   0.00731   0.00227  -0.0207   0.6557   0.7730
   2.250   0.3404   0.00731   0.00231  -0.0206   0.6436   0.7815
   2.500   0.3672   0.00733   0.00229  -0.0203   0.6240   0.7901
   2.750   0.3945   0.00733   0.00232  -0.0201   0.6044   0.7984
   3.000   0.4219   0.00738   0.00237  -0.0199   0.5867   0.8074
   3.250   0.4492   0.00743   0.00246  -0.0198   0.5728   0.8155
   3.500   0.4766   0.00750   0.00255  -0.0197   0.5557   0.8248
   3.750   0.5029   0.00760   0.00265  -0.0193   0.5327   0.8334
   4.000   0.5290   0.00774   0.00276  -0.0189   0.4989   0.8428
   4.250   0.5529   0.00812   0.00291  -0.0183   0.4261   0.8528
   4.500   0.5686   0.00945   0.00347  -0.0168   0.2465   0.8628
   4.750   0.5860   0.01067   0.00408  -0.0156   0.1154   0.8735
   5.000   0.6068   0.01143   0.00458  -0.0147   0.0619   0.8851
   5.250   0.6289   0.01185   0.00501  -0.0136   0.0497   0.8965
   5.500   0.6502   0.01231   0.00550  -0.0124   0.0428   0.9089
   5.750   0.6719   0.01262   0.00587  -0.0113   0.0386   0.9226
   6.000   0.6894   0.01329   0.00659  -0.0094   0.0345   0.9398
   6.250   0.7125   0.01360   0.00699  -0.0086   0.0327   0.9590
   6.500   0.7444   0.01415   0.00759  -0.0098   0.0302   0.9789
   6.750   0.7727   0.01498   0.00842  -0.0107   0.0282   1.0000
   7.000   0.7935   0.01596   0.00945  -0.0100   0.0266   1.0000
   7.250   0.8176   0.01651   0.01004  -0.0098   0.0254   1.0000
   7.500   0.8403   0.01724   0.01081  -0.0093   0.0244   1.0000
   7.750   0.8627   0.01798   0.01159  -0.0087   0.0235   1.0000
   8.000   0.8847   0.01877   0.01240  -0.0082   0.0227   1.0000
   8.250   0.9059   0.01980   0.01343  -0.0075   0.0220   1.0000
   8.500   0.9265   0.02176   0.01546  -0.0068   0.0213   1.0000
   8.750   0.9487   0.02305   0.01688  -0.0063   0.0208   1.0000
   9.000   0.9707   0.02386   0.01781  -0.0057   0.0203   1.0000
   9.250   0.9919   0.02500   0.01909  -0.0050   0.0196   1.0000
   9.500   1.0122   0.02654   0.02080  -0.0043   0.0192   1.0000
   9.750   1.0311   0.02811   0.02253  -0.0034   0.0187   1.0000
  10.000   1.0480   0.02995   0.02457  -0.0024   0.0185   1.0000
  10.250   1.0627   0.03193   0.02676  -0.0012   0.0182   1.0000
  10.500   1.0744   0.03411   0.02915   0.0002   0.0180   1.0000
  10.750   1.0821   0.03655   0.03183   0.0020   0.0178   1.0000
  11.000   1.0966   0.03720   0.03247   0.0029   0.0173   1.0000
  11.250   1.1035   0.03890   0.03426   0.0045   0.0169   1.0000
  11.500   1.0973   0.04195   0.03752   0.0073   0.0167   1.0000
  11.750   1.0829   0.04549   0.04131   0.0102   0.0166   1.0000
  12.000   1.0695   0.04867   0.04471   0.0124   0.0166   1.0000
  12.250   1.0531   0.05229   0.04855   0.0139   0.0165   1.0000
  12.500   1.0360   0.05617   0.05263   0.0144   0.0165   1.0000
  12.750   1.0215   0.05995   0.05658   0.0142   0.0166   1.0000
  13.000   1.0058   0.06412   0.06095   0.0132   0.0167   1.0000
  13.250   0.9818   0.07013   0.06713   0.0108   0.0167   1.0000
<< Back to NACA 64(1)-112 (naca641112-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(1)-112 (naca641112-il)