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NACA 64-110 AIRFOIL (n64110-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-110 AIRFOIL (n64110-il)
Reynolds number: 200,000
Max Cl/Cd: 44.62 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64110-il-200000-n5.txt
Download as CSV file: xf-n64110-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-110 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6633   0.08128   0.07780  -0.0177   1.0000   0.0158
 -10.250  -0.6849   0.07116   0.06762  -0.0258   1.0000   0.0156
 -10.000  -0.7057   0.06467   0.06103  -0.0304   1.0000   0.0152
  -9.750  -0.7272   0.05950   0.05574  -0.0324   1.0000   0.0149
  -9.500  -0.7465   0.05531   0.05138  -0.0319   1.0000   0.0151
  -9.250  -0.7582   0.05071   0.04651  -0.0313   1.0000   0.0153
  -9.000  -0.7652   0.04582   0.04127  -0.0303   1.0000   0.0158
  -8.750  -0.7662   0.04121   0.03622  -0.0290   1.0000   0.0161
  -8.500  -0.7616   0.03703   0.03156  -0.0277   1.0000   0.0163
  -8.250  -0.7513   0.03356   0.02759  -0.0264   1.0000   0.0167
  -8.000  -0.7372   0.03066   0.02424  -0.0252   1.0000   0.0172
  -7.750  -0.7209   0.02813   0.02147  -0.0245   1.0000   0.0179
  -7.500  -0.7006   0.02706   0.02029  -0.0240   1.0000   0.0189
  -7.250  -0.6798   0.02584   0.01890  -0.0234   1.0000   0.0199
  -7.000  -0.6587   0.02429   0.01712  -0.0226   1.0000   0.0209
  -6.750  -0.6372   0.02272   0.01533  -0.0217   1.0000   0.0216
  -6.500  -0.6157   0.02138   0.01381  -0.0207   1.0000   0.0224
  -6.250  -0.5946   0.02029   0.01257  -0.0197   1.0000   0.0232
  -6.000  -0.5740   0.01961   0.01175  -0.0185   1.0000   0.0242
  -5.750  -0.5499   0.01803   0.01015  -0.0185   0.9950   0.0260
  -5.500  -0.5171   0.01700   0.00908  -0.0200   0.9859   0.0274
  -5.250  -0.4846   0.01612   0.00814  -0.0215   0.9765   0.0291
  -5.000  -0.4523   0.01534   0.00726  -0.0228   0.9669   0.0313
  -4.750  -0.4201   0.01473   0.00655  -0.0240   0.9572   0.0337
  -4.500  -0.3893   0.01396   0.00577  -0.0251   0.9471   0.0390
  -4.250  -0.3586   0.01349   0.00521  -0.0259   0.9367   0.0443
  -4.000  -0.3303   0.01298   0.00467  -0.0262   0.9253   0.0534
  -3.750  -0.3030   0.01248   0.00423  -0.0263   0.9140   0.0748
  -3.500  -0.2785   0.01163   0.00376  -0.0263   0.9029   0.1618
  -3.250  -0.2588   0.01018   0.00329  -0.0258   0.8915   0.3902
  -3.000  -0.2355   0.00970   0.00319  -0.0250   0.8803   0.5108
  -2.750  -0.2100   0.00953   0.00312  -0.0243   0.8699   0.5622
  -2.500  -0.1858   0.00939   0.00318  -0.0233   0.8600   0.6281
  -2.250  -0.1618   0.00937   0.00330  -0.0220   0.8502   0.6785
  -2.000  -0.1357   0.00936   0.00325  -0.0214   0.8401   0.6979
  -1.750  -0.1088   0.00933   0.00316  -0.0210   0.8310   0.7085
  -1.500  -0.0816   0.00931   0.00306  -0.0208   0.8217   0.7185
  -1.250  -0.0546   0.00927   0.00300  -0.0205   0.8122   0.7261
  -1.000  -0.0273   0.00926   0.00292  -0.0203   0.8035   0.7347
  -0.750  -0.0002   0.00924   0.00288  -0.0200   0.7941   0.7432
  -0.500   0.0271   0.00923   0.00284  -0.0198   0.7856   0.7517
  -0.250   0.0544   0.00923   0.00281  -0.0196   0.7771   0.7606
   0.000   0.0815   0.00923   0.00282  -0.0194   0.7679   0.7690
   0.250   0.1087   0.00924   0.00281  -0.0191   0.7598   0.7786
   0.500   0.1358   0.00925   0.00285  -0.0189   0.7511   0.7877
   0.750   0.1629   0.00927   0.00289  -0.0186   0.7432   0.7966
   1.000   0.1901   0.00930   0.00293  -0.0184   0.7348   0.8065
   1.250   0.2168   0.00932   0.00301  -0.0181   0.7265   0.8159
   1.500   0.2436   0.00936   0.00308  -0.0177   0.7190   0.8257
   1.750   0.2706   0.00940   0.00318  -0.0175   0.7107   0.8360
   2.000   0.2969   0.00944   0.00327  -0.0170   0.7021   0.8460
   2.250   0.3230   0.00948   0.00337  -0.0164   0.6911   0.8563
   2.500   0.3490   0.00952   0.00346  -0.0159   0.6782   0.8672
   2.750   0.3730   0.00954   0.00341  -0.0147   0.6456   0.8789
   3.000   0.3956   0.00962   0.00334  -0.0132   0.5896   0.8907
   3.250   0.4197   0.00977   0.00338  -0.0122   0.5440   0.9030
   3.500   0.4444   0.00996   0.00349  -0.0115   0.4954   0.9163
   3.750   0.4645   0.01073   0.00364  -0.0103   0.3456   0.9314
   4.000   0.4844   0.01213   0.00424  -0.0098   0.1645   0.9484
   4.250   0.5121   0.01314   0.00481  -0.0107   0.0760   0.9647
   4.500   0.5446   0.01380   0.00536  -0.0122   0.0511   0.9830
   4.750   0.5734   0.01432   0.00590  -0.0129   0.0422   1.0000
   5.000   0.5958   0.01503   0.00661  -0.0123   0.0363   1.0000
   5.250   0.6196   0.01559   0.00726  -0.0118   0.0337   1.0000
   5.500   0.6428   0.01626   0.00799  -0.0113   0.0311   1.0000
   5.750   0.6656   0.01700   0.00876  -0.0108   0.0288   1.0000
   6.000   0.6862   0.01814   0.00989  -0.0100   0.0263   1.0000
   6.250   0.7095   0.01893   0.01078  -0.0095   0.0250   1.0000
   6.500   0.7325   0.01989   0.01183  -0.0089   0.0239   1.0000
   6.750   0.7556   0.02098   0.01301  -0.0083   0.0229   1.0000
   7.000   0.7790   0.02217   0.01431  -0.0077   0.0220   1.0000
   7.250   0.8023   0.02348   0.01574  -0.0072   0.0212   1.0000
   7.500   0.8254   0.02483   0.01726  -0.0067   0.0205   1.0000
   7.750   0.8476   0.02602   0.01855  -0.0063   0.0195   1.0000
   8.000   0.8679   0.02800   0.02064  -0.0058   0.0185   1.0000
   8.250   0.8880   0.02990   0.02284  -0.0050   0.0179   1.0000
   8.500   0.9064   0.03211   0.02542  -0.0040   0.0175   1.0000
   8.750   0.9217   0.03479   0.02851  -0.0028   0.0170   1.0000
   9.000   0.9329   0.03793   0.03208  -0.0014   0.0166   1.0000
   9.250   0.9410   0.04110   0.03569   0.0002   0.0159   1.0000
   9.500   0.9458   0.04426   0.03920   0.0018   0.0153   1.0000
   9.750   0.9522   0.04636   0.04151   0.0030   0.0145   1.0000
  10.000   0.9529   0.04901   0.04438   0.0045   0.0142   1.0000
  10.250   0.9439   0.05223   0.04784   0.0066   0.0140   1.0000
  10.500   0.9268   0.05593   0.05177   0.0085   0.0140   1.0000
  10.750   0.9116   0.05955   0.05556   0.0089   0.0139   1.0000
  11.000   0.8885   0.06486   0.06107   0.0076   0.0139   1.0000
  11.250   0.8497   0.07416   0.07063   0.0028   0.0142   1.0000
  11.500   0.8005   0.09020   0.08684  -0.0085   0.0148   1.0000
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