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NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 (n64212-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.16 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212-il-1000000.txt
Download as CSV file: xf-n64212-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8830   0.05972   0.05753  -0.0460   1.0000   0.0105
 -13.500  -0.9400   0.04844   0.04587  -0.0522   1.0000   0.0103
 -13.250  -0.9597   0.04343   0.04066  -0.0539   1.0000   0.0103
 -13.000  -0.9703   0.03991   0.03697  -0.0545   1.0000   0.0103
 -12.750  -0.9704   0.03783   0.03480  -0.0544   1.0000   0.0105
 -12.500  -0.9815   0.03474   0.03152  -0.0536   1.0000   0.0106
 -12.250  -0.9861   0.03254   0.02915  -0.0522   1.0000   0.0107
 -12.000  -0.9862   0.03101   0.02749  -0.0503   1.0000   0.0109
 -11.750  -0.9856   0.02969   0.02606  -0.0478   1.0000   0.0111
 -11.500  -0.9811   0.02797   0.02415  -0.0458   1.0000   0.0113
 -11.250  -0.9698   0.02671   0.02274  -0.0444   1.0000   0.0115
 -11.000  -0.9544   0.02588   0.02179  -0.0433   1.0000   0.0117
 -10.750  -0.9382   0.02503   0.02083  -0.0423   1.0000   0.0119
 -10.500  -0.9321   0.02212   0.01760  -0.0404   1.0000   0.0122
 -10.250  -0.9178   0.02058   0.01595  -0.0391   1.0000   0.0126
 -10.000  -0.8992   0.01978   0.01510  -0.0382   1.0000   0.0129
  -9.750  -0.8798   0.01918   0.01446  -0.0373   1.0000   0.0132
  -9.500  -0.8612   0.01853   0.01375  -0.0361   1.0000   0.0135
  -9.250  -0.8348   0.01784   0.01300  -0.0365   0.9957   0.0139
  -9.000  -0.8022   0.01702   0.01209  -0.0382   0.9887   0.0144
  -8.750  -0.7683   0.01626   0.01125  -0.0401   0.9819   0.0149
  -8.500  -0.7337   0.01585   0.01077  -0.0420   0.9728   0.0153
  -8.250  -0.7050   0.01461   0.00940  -0.0430   0.9599   0.0159
  -8.000  -0.6812   0.01369   0.00840  -0.0428   0.9441   0.0165
  -7.750  -0.6578   0.01324   0.00789  -0.0422   0.9294   0.0170
  -7.500  -0.6341   0.01287   0.00746  -0.0416   0.9163   0.0176
  -7.250  -0.6102   0.01250   0.00701  -0.0410   0.9041   0.0183
  -7.000  -0.5858   0.01213   0.00657  -0.0405   0.8931   0.0189
  -6.750  -0.5606   0.01187   0.00623  -0.0401   0.8825   0.0195
  -6.500  -0.5360   0.01142   0.00571  -0.0397   0.8722   0.0202
  -6.250  -0.5123   0.01081   0.00501  -0.0392   0.8627   0.0215
  -6.000  -0.4864   0.01052   0.00469  -0.0390   0.8531   0.0226
  -5.750  -0.4600   0.01026   0.00438  -0.0389   0.8443   0.0239
  -5.250  -0.4073   0.00964   0.00363  -0.0386   0.8271   0.0273
  -5.000  -0.3805   0.00941   0.00337  -0.0385   0.8187   0.0299
  -4.750  -0.3530   0.00923   0.00316  -0.0385   0.8100   0.0320
  -4.500  -0.3262   0.00893   0.00282  -0.0384   0.8020   0.0367
  -4.250  -0.2987   0.00875   0.00261  -0.0384   0.7937   0.0407
  -4.000  -0.2714   0.00850   0.00237  -0.0385   0.7859   0.0508
  -3.750  -0.2445   0.00814   0.00213  -0.0385   0.7777   0.0848
  -3.500  -0.2182   0.00760   0.00188  -0.0386   0.7700   0.1610
  -3.250  -0.1929   0.00681   0.00156  -0.0388   0.7618   0.2934
  -3.000  -0.1675   0.00601   0.00132  -0.0389   0.7540   0.4503
  -2.750  -0.1397   0.00584   0.00124  -0.0390   0.7458   0.4985
  -2.500  -0.1113   0.00574   0.00119  -0.0392   0.7382   0.5255
  -2.250  -0.0829   0.00570   0.00115  -0.0393   0.7305   0.5438
  -2.000  -0.0543   0.00565   0.00111  -0.0395   0.7231   0.5603
  -1.750  -0.0258   0.00563   0.00108  -0.0396   0.7156   0.5759
  -1.500   0.0028   0.00560   0.00107  -0.0398   0.7084   0.5970
  -1.250   0.0311   0.00557   0.00108  -0.0399   0.7010   0.6194
  -1.000   0.0598   0.00556   0.00108  -0.0400   0.6939   0.6313
  -0.750   0.0885   0.00557   0.00107  -0.0402   0.6864   0.6398
  -0.500   0.1172   0.00557   0.00106  -0.0404   0.6795   0.6475
  -0.250   0.1460   0.00558   0.00106  -0.0406   0.6725   0.6553
   0.000   0.1746   0.00559   0.00107  -0.0407   0.6661   0.6621
   0.250   0.2035   0.00560   0.00108  -0.0409   0.6594   0.6692
   0.500   0.2320   0.00564   0.00110  -0.0411   0.6528   0.6760
   0.750   0.2609   0.00563   0.00112  -0.0413   0.6456   0.6833
   1.250   0.3181   0.00568   0.00119  -0.0416   0.6306   0.6983
   1.750   0.3751   0.00574   0.00126  -0.0419   0.6128   0.7140
   2.000   0.4034   0.00579   0.00130  -0.0420   0.5987   0.7216
   2.250   0.4311   0.00587   0.00133  -0.0420   0.5788   0.7297
   2.500   0.4591   0.00594   0.00139  -0.0420   0.5629   0.7375
   2.750   0.4871   0.00602   0.00146  -0.0421   0.5472   0.7458
   3.000   0.5153   0.00608   0.00154  -0.0422   0.5337   0.7538
   3.250   0.5431   0.00618   0.00162  -0.0422   0.5153   0.7626
   3.500   0.5706   0.00630   0.00173  -0.0422   0.4927   0.7710
   3.750   0.5971   0.00655   0.00186  -0.0420   0.4503   0.7799
   4.000   0.6185   0.00739   0.00220  -0.0413   0.3281   0.7884
   4.250   0.6394   0.00834   0.00266  -0.0405   0.2111   0.7972
   4.500   0.6615   0.00911   0.00307  -0.0399   0.1272   0.8063
   4.750   0.6850   0.00969   0.00343  -0.0394   0.0758   0.8152
   5.000   0.7096   0.01013   0.00376  -0.0390   0.0492   0.8248
   5.250   0.7348   0.01044   0.00406  -0.0387   0.0394   0.8343
   5.500   0.7602   0.01074   0.00438  -0.0383   0.0339   0.8441
   5.750   0.7854   0.01103   0.00469  -0.0380   0.0301   0.8544
   6.000   0.8098   0.01136   0.00508  -0.0374   0.0267   0.8645
   6.250   0.8346   0.01162   0.00538  -0.0370   0.0244   0.8754
   6.500   0.8566   0.01216   0.00597  -0.0360   0.0214   0.8879
   7.000   0.9034   0.01268   0.00663  -0.0345   0.0195   0.9158
   7.250   0.9243   0.01299   0.00699  -0.0333   0.0185   0.9328
   7.500   0.9432   0.01335   0.00742  -0.0316   0.0176   0.9585
   7.750   0.9669   0.01423   0.00839  -0.0315   0.0166   1.0000
   8.000   0.9914   0.01463   0.00883  -0.0312   0.0162   1.0000
   8.250   1.0153   0.01506   0.00929  -0.0308   0.0157   1.0000
   8.500   1.0381   0.01556   0.00982  -0.0303   0.0151   1.0000
   8.750   1.0602   0.01610   0.01039  -0.0297   0.0146   1.0000
   9.000   1.0817   0.01666   0.01098  -0.0290   0.0142   1.0000
   9.250   1.1020   0.01729   0.01165  -0.0281   0.0138   1.0000
   9.500   1.1199   0.01811   0.01250  -0.0269   0.0134   1.0000
   9.750   1.1332   0.01934   0.01381  -0.0251   0.0130   1.0000
  10.000   1.1457   0.02074   0.01532  -0.0233   0.0127   1.0000
  10.250   1.1621   0.02153   0.01617  -0.0218   0.0126   1.0000
  10.500   1.1769   0.02226   0.01698  -0.0201   0.0125   1.0000
  10.750   1.1905   0.02309   0.01790  -0.0184   0.0123   1.0000
  11.000   1.2031   0.02404   0.01893  -0.0166   0.0121   1.0000
  11.250   1.2163   0.02477   0.01973  -0.0150   0.0118   1.0000
  11.500   1.2276   0.02582   0.02086  -0.0134   0.0115   1.0000
  11.750   1.2383   0.02693   0.02206  -0.0118   0.0114   1.0000
  12.000   1.2485   0.02804   0.02325  -0.0103   0.0111   1.0000
  12.250   1.2577   0.02927   0.02458  -0.0088   0.0110   1.0000
  12.500   1.2654   0.03071   0.02611  -0.0074   0.0108   1.0000
  12.750   1.2736   0.03199   0.02747  -0.0063   0.0106   1.0000
  13.000   1.2804   0.03349   0.02904  -0.0051   0.0104   1.0000
  13.250   1.2850   0.03528   0.03093  -0.0041   0.0103   1.0000
  13.500   1.2875   0.03738   0.03313  -0.0031   0.0102   1.0000
  13.750   1.2861   0.04002   0.03590  -0.0022   0.0100   1.0000
  14.000   1.2740   0.04412   0.04022  -0.0013   0.0098   1.0000
  14.250   1.2591   0.04864   0.04498  -0.0010   0.0098   1.0000
  14.500   1.2382   0.05407   0.05067  -0.0014   0.0097   1.0000
  14.750   1.2281   0.05828   0.05505  -0.0023   0.0097   1.0000
  15.000   1.2279   0.06122   0.05810  -0.0033   0.0096   1.0000
  15.250   1.2208   0.06539   0.06240  -0.0049   0.0095   1.0000
  15.500   1.2033   0.07153   0.06872  -0.0074   0.0095   1.0000
  15.750   1.1930   0.07688   0.07421  -0.0101   0.0095   1.0000
  16.000   1.1709   0.08477   0.08229  -0.0144   0.0095   1.0000
  16.250   1.1421   0.09470   0.09241  -0.0203   0.0095   1.0000
  16.500   1.1184   0.10459   0.10247  -0.0265   0.0095   1.0000
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