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NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-212 (naca651212-il)
Reynolds number: 500,000
Max Cl/Cd: 66.05 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651212-il-500000-n5.txt
Download as CSV file: xf-naca651212-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.8198   0.05598   0.05318  -0.0551   1.0000   0.0094
 -12.750  -0.8437   0.05012   0.04713  -0.0577   1.0000   0.0094
 -12.500  -0.8547   0.04653   0.04340  -0.0585   1.0000   0.0095
 -12.250  -0.8528   0.04479   0.04160  -0.0586   1.0000   0.0096
 -12.000  -0.8706   0.04093   0.03752  -0.0579   1.0000   0.0096
 -11.750  -0.8793   0.03833   0.03475  -0.0565   1.0000   0.0097
 -11.500  -0.8690   0.03798   0.03440  -0.0555   1.0000   0.0099
 -11.250  -0.8779   0.03571   0.03194  -0.0528   1.0000   0.0100
 -11.000  -0.8774   0.03433   0.03044  -0.0502   1.0000   0.0101
 -10.750  -0.8735   0.03263   0.02855  -0.0482   1.0000   0.0104
 -10.500  -0.8694   0.03067   0.02636  -0.0460   1.0000   0.0107
 -10.250  -0.8598   0.02855   0.02399  -0.0446   0.9963   0.0110
 -10.000  -0.8374   0.02614   0.02124  -0.0457   0.9813   0.0115
  -9.750  -0.8112   0.02425   0.01906  -0.0470   0.9707   0.0119
  -9.500  -0.7828   0.02304   0.01760  -0.0482   0.9610   0.0123
  -9.250  -0.7582   0.02147   0.01586  -0.0489   0.9502   0.0129
  -9.000  -0.7341   0.02073   0.01503  -0.0490   0.9388   0.0132
  -8.750  -0.7114   0.02002   0.01421  -0.0487   0.9278   0.0136
  -8.500  -0.6893   0.01928   0.01335  -0.0481   0.9174   0.0139
  -8.250  -0.6675   0.01858   0.01253  -0.0474   0.9073   0.0144
  -8.000  -0.6456   0.01781   0.01164  -0.0467   0.8980   0.0148
  -7.750  -0.6233   0.01717   0.01085  -0.0460   0.8893   0.0153
  -7.500  -0.6002   0.01663   0.01021  -0.0454   0.8804   0.0159
  -7.250  -0.5770   0.01610   0.00956  -0.0448   0.8725   0.0163
  -7.000  -0.5551   0.01533   0.00870  -0.0441   0.8643   0.0167
  -6.750  -0.5335   0.01459   0.00788  -0.0433   0.8567   0.0172
  -6.500  -0.5102   0.01409   0.00732  -0.0427   0.8488   0.0177
  -6.250  -0.4864   0.01366   0.00684  -0.0423   0.8416   0.0183
  -6.000  -0.4622   0.01325   0.00636  -0.0419   0.8343   0.0189
  -5.750  -0.4377   0.01288   0.00592  -0.0415   0.8280   0.0199
  -5.500  -0.4126   0.01254   0.00552  -0.0412   0.8209   0.0208
  -5.000  -0.3629   0.01176   0.00461  -0.0405   0.8077   0.0225
  -4.750  -0.3378   0.01139   0.00419  -0.0402   0.8014   0.0239
  -4.500  -0.3117   0.01112   0.00388  -0.0401   0.7956   0.0254
  -4.250  -0.2853   0.01088   0.00359  -0.0400   0.7894   0.0273
  -4.000  -0.2587   0.01069   0.00333  -0.0399   0.7838   0.0289
  -3.750  -0.2324   0.01040   0.00304  -0.0398   0.7776   0.0336
  -3.500  -0.2056   0.01021   0.00281  -0.0398   0.7717   0.0380
  -3.250  -0.1788   0.00998   0.00260  -0.0398   0.7664   0.0483
  -3.000  -0.1530   0.00956   0.00236  -0.0397   0.7608   0.0961
  -2.750  -0.1290   0.00884   0.00206  -0.0396   0.7555   0.2173
  -2.500  -0.1059   0.00790   0.00173  -0.0396   0.7501   0.3831
  -2.250  -0.0823   0.00718   0.00160  -0.0393   0.7445   0.5474
  -1.750  -0.0283   0.00695   0.00164  -0.0391   0.7348   0.6472
  -1.500  -0.0003   0.00695   0.00163  -0.0391   0.7296   0.6655
  -1.250   0.0277   0.00695   0.00162  -0.0392   0.7250   0.6763
  -1.000   0.0563   0.00695   0.00159  -0.0394   0.7202   0.6836
  -0.750   0.0848   0.00694   0.00158  -0.0395   0.7153   0.6880
  -0.500   0.1132   0.00696   0.00155  -0.0397   0.7107   0.6930
  -0.250   0.1419   0.00697   0.00155  -0.0400   0.7062   0.6978
   0.000   0.1703   0.00696   0.00156  -0.0402   0.7014   0.7022
   0.250   0.1988   0.00698   0.00157  -0.0403   0.6969   0.7072
   0.500   0.2274   0.00701   0.00158  -0.0406   0.6927   0.7122
   0.750   0.2558   0.00701   0.00162  -0.0408   0.6879   0.7166
   1.000   0.2842   0.00703   0.00166  -0.0409   0.6833   0.7217
   1.250   0.3126   0.00708   0.00169  -0.0411   0.6793   0.7269
   1.500   0.3410   0.00709   0.00176  -0.0413   0.6746   0.7316
   1.750   0.3693   0.00711   0.00182  -0.0415   0.6695   0.7370
   2.000   0.3973   0.00715   0.00186  -0.0415   0.6592   0.7424
   2.250   0.4246   0.00719   0.00191  -0.0414   0.6451   0.7472
   2.500   0.4516   0.00725   0.00195  -0.0413   0.6251   0.7529
   2.750   0.4772   0.00739   0.00198  -0.0409   0.5877   0.7587
   3.000   0.5020   0.00760   0.00206  -0.0403   0.5397   0.7642
   3.250   0.5216   0.00829   0.00227  -0.0391   0.4253   0.7703
   3.500   0.5384   0.00939   0.00277  -0.0377   0.2837   0.7761
   3.750   0.5570   0.01032   0.00323  -0.0365   0.1704   0.7827
   4.000   0.5772   0.01110   0.00365  -0.0356   0.0867   0.7894
   4.250   0.5997   0.01161   0.00401  -0.0349   0.0476   0.7959
   4.500   0.6240   0.01196   0.00433  -0.0345   0.0356   0.8028
   4.750   0.6487   0.01223   0.00463  -0.0341   0.0306   0.8090
   5.000   0.6730   0.01255   0.00496  -0.0336   0.0272   0.8163
   5.250   0.6967   0.01289   0.00536  -0.0330   0.0245   0.8233
   5.500   0.7208   0.01319   0.00572  -0.0325   0.0230   0.8312
   5.750   0.7442   0.01352   0.00611  -0.0319   0.0214   0.8386
   6.000   0.7669   0.01390   0.00654  -0.0311   0.0201   0.8467
   6.250   0.7874   0.01444   0.00714  -0.0300   0.0188   0.8547
   6.750   0.8300   0.01527   0.00813  -0.0280   0.0174   0.8733
   7.000   0.8506   0.01568   0.00861  -0.0269   0.0167   0.8832
   7.250   0.8702   0.01615   0.00915  -0.0257   0.0161   0.8939
   7.500   0.8886   0.01663   0.00972  -0.0242   0.0156   0.9060
   7.750   0.9061   0.01712   0.01027  -0.0226   0.0151   0.9199
   8.000   0.9223   0.01765   0.01088  -0.0208   0.0148   0.9368
   8.250   0.9407   0.01834   0.01165  -0.0195   0.0144   0.9593
   8.500   0.9611   0.01943   0.01281  -0.0191   0.0139   1.0000
   8.750   0.9790   0.02017   0.01362  -0.0179   0.0138   1.0000
   9.000   0.9967   0.02093   0.01446  -0.0167   0.0136   1.0000
   9.250   1.0140   0.02175   0.01537  -0.0155   0.0133   1.0000
   9.500   1.0314   0.02252   0.01622  -0.0143   0.0129   1.0000
   9.750   1.0482   0.02346   0.01725  -0.0131   0.0126   1.0000
  10.000   1.0646   0.02432   0.01820  -0.0119   0.0122   1.0000
  10.250   1.0804   0.02536   0.01935  -0.0107   0.0120   1.0000
  10.500   1.0954   0.02632   0.02041  -0.0094   0.0117   1.0000
  10.750   1.1096   0.02747   0.02166  -0.0081   0.0115   1.0000
  11.000   1.1229   0.02856   0.02285  -0.0068   0.0113   1.0000
  11.250   1.1350   0.02971   0.02410  -0.0055   0.0111   1.0000
  11.500   1.1461   0.03090   0.02538  -0.0042   0.0109   1.0000
  11.750   1.1554   0.03232   0.02690  -0.0028   0.0107   1.0000
  12.000   1.1617   0.03416   0.02887  -0.0014   0.0105   1.0000
  12.250   1.1661   0.03617   0.03109   0.0001   0.0103   1.0000
  12.500   1.1707   0.03804   0.03315   0.0015   0.0101   1.0000
  12.750   1.1729   0.04020   0.03551   0.0027   0.0100   1.0000
  13.000   1.1716   0.04280   0.03832   0.0040   0.0098   1.0000
  13.250   1.1696   0.04545   0.04119   0.0049   0.0096   1.0000
  13.500   1.1619   0.04888   0.04485   0.0056   0.0095   1.0000
  13.750   1.1494   0.05301   0.04923   0.0060   0.0094   1.0000
  14.000   1.1363   0.05738   0.05381   0.0057   0.0093   1.0000
  14.250   1.1204   0.06234   0.05900   0.0047   0.0092   1.0000
  14.500   1.0968   0.06884   0.06574   0.0027   0.0092   1.0000
  14.750   1.0756   0.07555   0.07265  -0.0002   0.0091   1.0000
  15.000   1.0443   0.08501   0.08235  -0.0054   0.0092   1.0000
  15.250   1.0041   0.09814   0.09573  -0.0137   0.0092   1.0000
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