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


Details Polar file
Airfoil: NACA 64(1)-112 (naca641112-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.64 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca641112-il-1000000.txt
Download as CSV file: xf-naca641112-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.9869   0.06895   0.06664  -0.0296   1.0000   0.0098
 -14.750  -1.0109   0.06150   0.05902  -0.0341   1.0000   0.0099
 -14.500  -1.0311   0.05531   0.05265  -0.0374   1.0000   0.0099
 -14.250  -1.0418   0.05095   0.04816  -0.0393   1.0000   0.0099
 -14.000  -1.0334   0.04931   0.04652  -0.0401   1.0000   0.0101
 -13.750  -1.0585   0.04361   0.04056  -0.0415   1.0000   0.0101
 -13.500  -1.0612   0.04096   0.03781  -0.0418   1.0000   0.0102
 -13.250  -1.0674   0.03805   0.03473  -0.0416   1.0000   0.0102
 -13.000  -1.0670   0.03606   0.03263  -0.0411   1.0000   0.0104
 -12.750  -1.0645   0.03441   0.03089  -0.0402   1.0000   0.0106
 -12.500  -1.0618   0.03284   0.02922  -0.0391   1.0000   0.0108
 -12.250  -1.0628   0.03092   0.02714  -0.0373   1.0000   0.0109
 -12.000  -1.0600   0.02951   0.02561  -0.0353   1.0000   0.0111
 -11.750  -1.0572   0.02815   0.02412  -0.0329   1.0000   0.0113
 -11.500  -1.0488   0.02693   0.02277  -0.0309   1.0000   0.0115
 -11.250  -1.0355   0.02589   0.02160  -0.0296   1.0000   0.0117
 -11.000  -1.0197   0.02503   0.02063  -0.0285   1.0000   0.0119
 -10.750  -1.0018   0.02437   0.01987  -0.0276   1.0000   0.0121
 -10.500  -0.9910   0.02205   0.01731  -0.0261   1.0000   0.0124
 -10.250  -0.9766   0.02035   0.01548  -0.0248   1.0000   0.0128
 -10.000  -0.9572   0.01950   0.01459  -0.0240   1.0000   0.0131
  -9.750  -0.9363   0.01886   0.01391  -0.0234   1.0000   0.0135
  -9.500  -0.9150   0.01821   0.01320  -0.0228   1.0000   0.0138
  -9.250  -0.8933   0.01756   0.01250  -0.0222   1.0000   0.0142
  -9.000  -0.8716   0.01689   0.01177  -0.0215   1.0000   0.0146
  -8.750  -0.8492   0.01636   0.01120  -0.0210   1.0000   0.0150
  -8.500  -0.8197   0.01584   0.01063  -0.0219   0.9888   0.0155
  -8.250  -0.7843   0.01531   0.01002  -0.0239   0.9752   0.0158
  -8.000  -0.7575   0.01390   0.00849  -0.0247   0.9573   0.0165
  -7.750  -0.7353   0.01330   0.00782  -0.0239   0.9390   0.0171
  -7.500  -0.7128   0.01291   0.00737  -0.0231   0.9236   0.0177
  -7.250  -0.6898   0.01255   0.00694  -0.0223   0.9101   0.0183
  -6.750  -0.6412   0.01192   0.00617  -0.0213   0.8865   0.0198
  -6.500  -0.6156   0.01170   0.00590  -0.0209   0.8762   0.0203
  -6.250  -0.5933   0.01099   0.00507  -0.0202   0.8658   0.0218
  -6.000  -0.5677   0.01067   0.00472  -0.0199   0.8558   0.0232
  -5.750  -0.5416   0.01041   0.00442  -0.0197   0.8469   0.0245
  -5.500  -0.5151   0.01022   0.00416  -0.0195   0.8379   0.0258
  -5.250  -0.4894   0.00979   0.00369  -0.0193   0.8289   0.0287
  -5.000  -0.4628   0.00958   0.00344  -0.0191   0.8203   0.0317
  -4.750  -0.4359   0.00934   0.00316  -0.0191   0.8113   0.0350
  -4.500  -0.4091   0.00909   0.00289  -0.0190   0.8031   0.0406
  -4.250  -0.3821   0.00883   0.00265  -0.0189   0.7946   0.0501
  -4.000  -0.3555   0.00849   0.00240  -0.0189   0.7867   0.0785
  -3.750  -0.3301   0.00793   0.00212  -0.0188   0.7783   0.1476
  -3.500  -0.3055   0.00716   0.00178  -0.0188   0.7703   0.2632
  -3.250  -0.2817   0.00625   0.00145  -0.0187   0.7620   0.4197
  -3.000  -0.2546   0.00595   0.00135  -0.0187   0.7539   0.4860
  -2.750  -0.2267   0.00584   0.00127  -0.0188   0.7458   0.5172
  -2.500  -0.1983   0.00576   0.00122  -0.0189   0.7379   0.5366
  -2.000  -0.1414   0.00567   0.00113  -0.0192   0.7226   0.5687
  -1.500  -0.0846   0.00559   0.00110  -0.0194   0.7078   0.6086
  -1.250  -0.0562   0.00559   0.00109  -0.0195   0.7004   0.6240
  -1.000  -0.0275   0.00556   0.00108  -0.0197   0.6930   0.6332
  -0.500   0.0299   0.00555   0.00105  -0.0200   0.6786   0.6488
   0.000   0.0874   0.00556   0.00105  -0.0204   0.6653   0.6631
   0.250   0.1163   0.00558   0.00106  -0.0206   0.6585   0.6702
   0.500   0.1449   0.00558   0.00107  -0.0208   0.6517   0.6769
   0.750   0.1737   0.00560   0.00108  -0.0210   0.6439   0.6843
   1.000   0.2023   0.00562   0.00111  -0.0211   0.6365   0.6914
   1.250   0.2310   0.00563   0.00114  -0.0213   0.6289   0.6993
   1.500   0.2596   0.00565   0.00117  -0.0214   0.6204   0.7068
   1.750   0.2879   0.00570   0.00120  -0.0215   0.6073   0.7148
   2.000   0.3161   0.00573   0.00122  -0.0216   0.5870   0.7222
   2.250   0.3443   0.00580   0.00126  -0.0217   0.5696   0.7303
   2.500   0.3724   0.00586   0.00131  -0.0217   0.5528   0.7379
   2.750   0.4007   0.00593   0.00138  -0.0219   0.5390   0.7461
   3.000   0.4287   0.00600   0.00146  -0.0219   0.5217   0.7540
   3.250   0.4566   0.00613   0.00154  -0.0220   0.4986   0.7626
   3.500   0.4836   0.00631   0.00166  -0.0219   0.4615   0.7709
   3.750   0.5071   0.00701   0.00191  -0.0215   0.3467   0.7795
   4.000   0.5285   0.00798   0.00235  -0.0209   0.2146   0.7880
   4.250   0.5518   0.00870   0.00272  -0.0205   0.1285   0.7965
   4.500   0.5761   0.00926   0.00306  -0.0201   0.0735   0.8053
   4.750   0.6012   0.00968   0.00336  -0.0199   0.0468   0.8139
   5.000   0.6274   0.00996   0.00363  -0.0197   0.0388   0.8233
   5.250   0.6532   0.01024   0.00395  -0.0194   0.0337   0.8325
   5.500   0.6792   0.01049   0.00422  -0.0192   0.0306   0.8420
   5.750   0.7039   0.01089   0.00467  -0.0187   0.0269   0.8520
   6.000   0.7296   0.01111   0.00494  -0.0184   0.0253   0.8618
   6.250   0.7547   0.01138   0.00525  -0.0180   0.0234   0.8724
   6.500   0.7771   0.01195   0.00588  -0.0172   0.0211   0.8844
   6.750   0.8014   0.01219   0.00620  -0.0166   0.0204   0.8966
   7.000   0.8247   0.01248   0.00655  -0.0158   0.0194   0.9099
   7.250   0.8470   0.01279   0.00693  -0.0149   0.0186   0.9251
   7.750   0.8901   0.01369   0.00797  -0.0129   0.0170   0.9711
   8.000   0.9159   0.01465   0.00901  -0.0133   0.0163   1.0000
   8.250   0.9398   0.01512   0.00953  -0.0129   0.0160   1.0000
   8.500   0.9635   0.01559   0.01003  -0.0125   0.0155   1.0000
   8.750   0.9864   0.01611   0.01059  -0.0120   0.0150   1.0000
   9.000   1.0082   0.01671   0.01123  -0.0114   0.0146   1.0000
   9.250   1.0304   0.01724   0.01179  -0.0108   0.0141   1.0000
   9.500   1.0511   0.01788   0.01247  -0.0101   0.0138   1.0000
   9.750   1.0709   0.01857   0.01319  -0.0092   0.0134   1.0000
  10.000   1.0874   0.01964   0.01432  -0.0079   0.0131   1.0000
  10.250   1.0973   0.02189   0.01672  -0.0060   0.0126   1.0000
  10.500   1.1159   0.02260   0.01751  -0.0050   0.0125   1.0000
  10.750   1.1329   0.02346   0.01847  -0.0038   0.0124   1.0000
  11.000   1.1479   0.02411   0.01920  -0.0023   0.0121   1.0000
  11.250   1.1605   0.02486   0.02003  -0.0005   0.0119   1.0000
  11.500   1.1712   0.02588   0.02115   0.0014   0.0117   1.0000
  11.750   1.1809   0.02697   0.02234   0.0033   0.0115   1.0000
  12.000   1.1893   0.02822   0.02369   0.0050   0.0113   1.0000
  12.250   1.1970   0.02950   0.02508   0.0066   0.0111   1.0000
  12.500   1.2041   0.03080   0.02649   0.0081   0.0109   1.0000
  12.750   1.2099   0.03228   0.02807   0.0094   0.0107   1.0000
  13.000   1.2138   0.03402   0.02992   0.0107   0.0106   1.0000
  13.250   1.2215   0.03520   0.03115   0.0115   0.0104   1.0000
  13.500   1.2212   0.03754   0.03364   0.0125   0.0103   1.0000
  13.750   1.2230   0.03961   0.03580   0.0131   0.0102   1.0000
  14.000   1.2229   0.04194   0.03821   0.0134   0.0100   1.0000
  14.250   1.2180   0.04505   0.04147   0.0136   0.0100   1.0000
  14.500   1.2080   0.04887   0.04544   0.0133   0.0098   1.0000
  14.750   1.1968   0.05308   0.04982   0.0125   0.0098   1.0000
  15.000   1.1679   0.05995   0.05694   0.0105   0.0097   1.0000
  15.250   1.1556   0.06492   0.06206   0.0084   0.0097   1.0000
  15.500   1.1370   0.07132   0.06863   0.0053   0.0097   1.0000
  15.750   1.1074   0.08024   0.07778   0.0003   0.0096   1.0000
  16.000   1.0926   0.08729   0.08496  -0.0040   0.0097   1.0000
  16.250   1.0633   0.09816   0.09602  -0.0111   0.0097   1.0000
  16.500   1.0447   0.10765   0.10565  -0.0173   0.0097   1.0000
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