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NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-112 (naca641112-il)
Reynolds number: 100,000
Max Cl/Cd: 44.13 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca641112-il-100000.txt
Download as CSV file: xf-naca641112-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5899   0.09785   0.09297  -0.0138   1.0000   0.1656
  -9.750  -0.5751   0.09497   0.09005  -0.0127   1.0000   0.1719
  -9.500  -0.5922   0.08974   0.08492  -0.0163   1.0000   0.1807
  -9.250  -0.6029   0.08560   0.08085  -0.0190   1.0000   0.1908
  -9.000  -0.5898   0.08219   0.07746  -0.0176   1.0000   0.1978
  -8.250  -0.7417   0.04964   0.04333  -0.0324   1.0000   0.0939
  -8.000  -0.7345   0.04413   0.03695  -0.0299   1.0000   0.0762
  -7.750  -0.7210   0.04019   0.03278  -0.0288   1.0000   0.0739
  -7.500  -0.7074   0.03692   0.02914  -0.0272   1.0000   0.0720
  -7.250  -0.6926   0.03425   0.02611  -0.0254   1.0000   0.0716
  -7.000  -0.6776   0.03227   0.02383  -0.0235   1.0000   0.0733
  -6.750  -0.6623   0.03041   0.02167  -0.0214   1.0000   0.0746
  -6.500  -0.6463   0.02864   0.01964  -0.0194   1.0000   0.0752
  -6.250  -0.6303   0.02714   0.01789  -0.0172   1.0000   0.0764
  -6.000  -0.6140   0.02571   0.01630  -0.0152   1.0000   0.0783
  -5.750  -0.5981   0.02414   0.01486  -0.0136   1.0000   0.0825
  -5.500  -0.5829   0.02318   0.01387  -0.0116   1.0000   0.0873
  -5.250  -0.5671   0.02233   0.01290  -0.0096   1.0000   0.0911
  -5.000  -0.5536   0.02109   0.01186  -0.0076   1.0000   0.0976
  -4.750  -0.5399   0.02030   0.01109  -0.0056   1.0000   0.1068
  -4.500  -0.5263   0.01948   0.01034  -0.0038   1.0000   0.1191
  -4.250  -0.5135   0.01842   0.00951  -0.0021   1.0000   0.1432
  -4.000  -0.5022   0.01529   0.00886  -0.0008   0.9959   0.5510
  -3.750  -0.4678   0.01613   0.00983  -0.0007   0.9864   0.6501
  -3.500  -0.4329   0.01687   0.01051  -0.0011   0.9773   0.6897
  -3.250  -0.3977   0.01779   0.01141  -0.0009   0.9691   0.7228
  -3.000  -0.3707   0.01892   0.01256   0.0018   0.9598   0.7565
  -2.750  -0.3440   0.01992   0.01354   0.0045   0.9512   0.7843
  -2.500  -0.3075   0.02039   0.01392   0.0040   0.9442   0.8014
  -2.250  -0.2756   0.02037   0.01375   0.0029   0.9353   0.8122
  -2.000  -0.2330   0.02039   0.01365   0.0000   0.9293   0.8209
  -1.750  -0.2013   0.02037   0.01354  -0.0010   0.9205   0.8294
  -1.500  -0.1599   0.02029   0.01334  -0.0040   0.9143   0.8391
  -1.250  -0.1293   0.02032   0.01332  -0.0045   0.9058   0.8461
  -1.000  -0.0928   0.02019   0.01311  -0.0067   0.8994   0.8552
  -0.750  -0.0627   0.02023   0.01311  -0.0073   0.8909   0.8621
  -0.500  -0.0276   0.02011   0.01294  -0.0090   0.8844   0.8708
  -0.250   0.0014   0.02017   0.01298  -0.0095   0.8760   0.8783
   0.000   0.0352   0.02011   0.01290  -0.0108   0.8697   0.8871
   0.250   0.0645   0.02017   0.01296  -0.0115   0.8617   0.8958
   0.500   0.1005   0.02014   0.01293  -0.0132   0.8552   0.9036
   0.750   0.1267   0.02022   0.01302  -0.0134   0.8477   0.9145
   1.000   0.1707   0.02026   0.01310  -0.0167   0.8415   0.9209
   1.250   0.2091   0.02019   0.01305  -0.0188   0.8367   0.9299
   1.500   0.2482   0.02038   0.01332  -0.0218   0.8280   0.9375
   1.750   0.2919   0.02028   0.01327  -0.0248   0.8228   0.9454
   2.000   0.3359   0.02040   0.01350  -0.0287   0.8140   0.9530
   2.250   0.3819   0.02024   0.01342  -0.0321   0.8079   0.9601
   2.500   0.4231   0.02036   0.01369  -0.0356   0.7988   0.9690
   2.750   0.4708   0.02013   0.01358  -0.0393   0.7922   0.9760
   3.000   0.5120   0.02009   0.01369  -0.0423   0.7808   0.9852
   3.250   0.5542   0.01924   0.01295  -0.0436   0.7638   0.9934
   3.500   0.5863   0.01801   0.01174  -0.0423   0.7373   1.0000
   3.750   0.5992   0.01707   0.01074  -0.0378   0.7138   1.0000
   4.000   0.6111   0.01653   0.01023  -0.0342   0.6890   1.0000
   4.250   0.6250   0.01606   0.00977  -0.0309   0.6665   1.0000
   4.500   0.6384   0.01565   0.00940  -0.0277   0.6408   1.0000
   4.750   0.6503   0.01527   0.00903  -0.0241   0.6064   1.0000
   5.000   0.6593   0.01494   0.00864  -0.0200   0.5477   1.0000
   5.250   0.6481   0.01597   0.00833  -0.0128   0.2919   1.0000
   5.500   0.6394   0.01866   0.00976  -0.0081   0.1476   1.0000
   5.750   0.6499   0.02014   0.01095  -0.0057   0.1199   1.0000
   6.000   0.6662   0.02139   0.01207  -0.0041   0.1043   1.0000
   6.250   0.6860   0.02270   0.01323  -0.0030   0.0945   1.0000
   6.500   0.7099   0.02406   0.01459  -0.0022   0.0868   1.0000
   6.750   0.7357   0.02589   0.01623  -0.0021   0.0799   1.0000
   7.000   0.7637   0.02758   0.01808  -0.0018   0.0768   1.0000
   7.250   0.7907   0.02935   0.02003  -0.0014   0.0734   1.0000
   7.500   0.8157   0.03110   0.02185  -0.0012   0.0695   1.0000
   7.750   0.8413   0.03382   0.02466  -0.0011   0.0674   1.0000
   8.000   0.8645   0.03710   0.02822  -0.0006   0.0669   1.0000
   8.250   0.8851   0.03982   0.03130   0.0004   0.0671   1.0000
   8.500   0.9031   0.04228   0.03423   0.0018   0.0681   1.0000
   8.750   0.9120   0.04565   0.03829   0.0040   0.0696   1.0000
   9.000   0.9150   0.05007   0.04335   0.0063   0.0724   1.0000
   9.250   0.9168   0.05480   0.04849   0.0080   0.0756   1.0000
   9.500   0.8416   0.05152   0.04627   0.0139   0.0858   1.0000
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