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NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-112 (naca641112-il)
Reynolds number: 50,000
Max Cl/Cd: 29.69 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca641112-il-50000.txt
Download as CSV file: xf-naca641112-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4968   0.08565   0.07915  -0.0203   1.0000   0.1947
  -9.250  -0.5517   0.07163   0.06521  -0.0309   1.0000   0.1599
  -9.000  -0.6792   0.07460   0.06788  -0.0307   1.0000   0.1653
  -8.750  -0.6963   0.06835   0.06148  -0.0325   1.0000   0.1528
  -8.500  -0.7117   0.06296   0.05579  -0.0331   1.0000   0.1435
  -8.250  -0.7365   0.05812   0.05011  -0.0323   1.0000   0.1337
  -8.000  -0.7210   0.05353   0.04548  -0.0319   1.0000   0.1304
  -7.750  -0.7137   0.04951   0.04110  -0.0308   1.0000   0.1271
  -7.500  -0.7054   0.04579   0.03688  -0.0294   1.0000   0.1240
  -7.250  -0.6925   0.04273   0.03342  -0.0280   1.0000   0.1244
  -7.000  -0.6774   0.04010   0.03048  -0.0265   1.0000   0.1270
  -6.750  -0.6610   0.03758   0.02760  -0.0249   1.0000   0.1291
  -6.500  -0.6425   0.03523   0.02485  -0.0233   1.0000   0.1307
  -6.250  -0.6234   0.03326   0.02245  -0.0216   1.0000   0.1337
  -6.000  -0.6017   0.03114   0.02048  -0.0204   1.0000   0.1417
  -5.750  -0.5794   0.02946   0.01863  -0.0189   1.0000   0.1498
  -5.500  -0.5565   0.02790   0.01713  -0.0174   1.0000   0.1614
  -5.250  -0.5372   0.02649   0.01584  -0.0154   1.0000   0.1789
  -5.000  -0.5232   0.02502   0.01464  -0.0129   1.0000   0.2015
  -4.750  -0.5166   0.02322   0.01333  -0.0098   1.0000   0.2458
  -4.500  -0.5285   0.02068   0.01320  -0.0027   1.0000   0.5204
  -4.250  -0.5361   0.02291   0.01570   0.0097   1.0000   0.6735
  -4.000  -0.5306   0.02488   0.01758   0.0190   1.0000   0.7271
  -3.750  -0.3104   0.03220   0.02362   0.0096   1.0000   0.8690
  -3.500  -0.2486   0.03129   0.02236   0.0033   1.0000   0.8917
  -3.250  -0.2201   0.03055   0.02143   0.0018   1.0000   0.9080
  -3.000  -0.1958   0.02987   0.02062   0.0007   1.0000   0.9220
  -2.750  -0.1739   0.02926   0.01990  -0.0003   1.0000   0.9346
  -2.500  -0.1541   0.02873   0.01928  -0.0011   1.0000   0.9465
  -2.250  -0.1333   0.02828   0.01872  -0.0022   1.0000   0.9581
  -2.000  -0.1026   0.02774   0.01809  -0.0051   1.0000   0.9694
  -1.750  -0.0705   0.02726   0.01752  -0.0085   1.0000   0.9802
  -1.500  -0.0373   0.02684   0.01702  -0.0123   1.0000   0.9909
  -1.250  -0.0075   0.02656   0.01668  -0.0157   1.0000   1.0000
  -1.000  -0.0155   0.02666   0.01678  -0.0124   1.0000   1.0000
  -0.750  -0.0232   0.02669   0.01681  -0.0093   1.0000   1.0000
  -0.500  -0.0308   0.02667   0.01678  -0.0062   1.0000   1.0000
  -0.250  -0.0385   0.02658   0.01668  -0.0031   1.0000   1.0000
   0.000  -0.0465   0.02643   0.01651   0.0001   1.0000   1.0000
   0.250  -0.0552   0.02619   0.01626   0.0034   1.0000   1.0000
   0.500  -0.0646   0.02588   0.01593   0.0068   1.0000   1.0000
   0.750  -0.0554   0.02585   0.01586   0.0071   0.9957   1.0000
   1.000  -0.0321   0.02612   0.01610   0.0050   0.9870   1.0000
   1.250  -0.0122   0.02642   0.01636   0.0037   0.9787   1.0000
   1.500   0.0126   0.02695   0.01686   0.0017   0.9705   1.0000
   1.750   0.0290   0.02728   0.01715   0.0013   0.9622   1.0000
   2.000   0.0573   0.02801   0.01786  -0.0009   0.9540   1.0000
   2.250   0.0846   0.02874   0.01857  -0.0028   0.9452   1.0000
   2.500   0.1110   0.02951   0.01935  -0.0044   0.9365   1.0000
   2.750   0.1483   0.03061   0.02048  -0.0079   0.9272   1.0000
   3.000   0.1699   0.03133   0.02123  -0.0086   0.9173   1.0000
   3.250   0.1983   0.03230   0.02227  -0.0103   0.9073   1.0000
   3.500   0.2339   0.03345   0.02351  -0.0132   0.8964   1.0000
   3.750   0.2625   0.03444   0.02460  -0.0148   0.8841   1.0000
   4.000   0.2902   0.03544   0.02572  -0.0161   0.8705   1.0000
   4.250   0.3232   0.03651   0.02696  -0.0181   0.8549   1.0000
   4.500   0.3661   0.03760   0.02828  -0.0211   0.8367   1.0000
   4.750   0.3906   0.03842   0.02928  -0.0213   0.8158   1.0000
   5.000   0.4421   0.03898   0.03019  -0.0241   0.7890   1.0000
   5.250   0.5212   0.03732   0.02912  -0.0266   0.7409   1.0000
   5.500   0.6572   0.02550   0.01826  -0.0194   0.6325   1.0000
   5.750   0.6580   0.02216   0.01375  -0.0056   0.3549   1.0000
   6.000   0.6496   0.02538   0.01530  -0.0007   0.2297   1.0000
   6.250   0.6645   0.02762   0.01703   0.0014   0.1892   1.0000
   6.500   0.6934   0.02964   0.01872   0.0019   0.1629   1.0000
   6.750   0.7293   0.03175   0.02081   0.0017   0.1468   1.0000
   7.000   0.7626   0.03417   0.02310   0.0014   0.1348   1.0000
   7.250   0.7902   0.03650   0.02588   0.0021   0.1297   1.0000
   7.500   0.8161   0.03903   0.02854   0.0024   0.1236   1.0000
   7.750   0.8387   0.04214   0.03187   0.0030   0.1196   1.0000
   8.000   0.8574   0.04530   0.03553   0.0041   0.1190   1.0000
   8.250   0.8739   0.04885   0.03948   0.0052   0.1193   1.0000
   8.500   0.8871   0.05260   0.04362   0.0063   0.1197   1.0000
   8.750   0.8959   0.05648   0.04789   0.0075   0.1200   1.0000
   9.000   0.9031   0.06064   0.05238   0.0085   0.1204   1.0000
   9.250   0.8793   0.06463   0.05721   0.0110   0.1256   1.0000
   9.500   0.8626   0.06958   0.06250   0.0118   0.1297   1.0000
   9.750   0.8539   0.07450   0.06757   0.0121   0.1326   1.0000
  10.000   0.8027   0.08023   0.07352   0.0112   0.1402   1.0000
  10.250   0.7796   0.08725   0.08056   0.0082   0.1471   1.0000
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