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NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-212 AIRFOIL (n63212-il)
Reynolds number: 100,000
Max Cl/Cd: 46.87 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63212-il-100000-n5.txt
Download as CSV file: xf-n63212-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-212 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6133   0.09081   0.08555  -0.0275   1.0000   0.0294
 -11.250  -0.6318   0.08213   0.07683  -0.0337   1.0000   0.0292
 -11.000  -0.6529   0.07453   0.06916  -0.0393   1.0000   0.0289
 -10.750  -0.6702   0.06874   0.06328  -0.0432   1.0000   0.0285
 -10.500  -0.6922   0.06336   0.05774  -0.0464   1.0000   0.0286
 -10.250  -0.7097   0.05921   0.05345  -0.0476   1.0000   0.0284
 -10.000  -0.7266   0.05576   0.04981  -0.0471   1.0000   0.0284
  -9.750  -0.7378   0.05231   0.04609  -0.0463   1.0000   0.0286
  -9.500  -0.7416   0.04899   0.04249  -0.0454   1.0000   0.0286
  -9.250  -0.7412   0.04574   0.03890  -0.0443   1.0000   0.0287
  -9.000  -0.7362   0.04266   0.03547  -0.0432   1.0000   0.0288
  -8.750  -0.7274   0.03988   0.03233  -0.0421   1.0000   0.0289
  -8.500  -0.7158   0.03729   0.02939  -0.0409   1.0000   0.0291
  -8.250  -0.7018   0.03500   0.02675  -0.0397   1.0000   0.0293
  -8.000  -0.6861   0.03299   0.02443  -0.0384   1.0000   0.0296
  -7.750  -0.6696   0.03111   0.02234  -0.0371   1.0000   0.0300
  -7.500  -0.6534   0.02931   0.02046  -0.0358   1.0000   0.0306
  -7.250  -0.6377   0.02792   0.01901  -0.0342   1.0000   0.0312
  -7.000  -0.6233   0.02681   0.01786  -0.0325   1.0000   0.0323
  -6.750  -0.6099   0.02590   0.01688  -0.0305   1.0000   0.0337
  -6.500  -0.5857   0.02479   0.01566  -0.0306   0.9956   0.0356
  -6.250  -0.5519   0.02354   0.01427  -0.0322   0.9874   0.0376
  -6.000  -0.5198   0.02217   0.01288  -0.0339   0.9790   0.0397
  -5.750  -0.4866   0.02106   0.01173  -0.0357   0.9710   0.0431
  -5.500  -0.4524   0.02008   0.01062  -0.0376   0.9635   0.0488
  -5.250  -0.4213   0.01913   0.00964  -0.0390   0.9541   0.0583
  -5.000  -0.3896   0.01819   0.00881  -0.0405   0.9457   0.0797
  -4.750  -0.3608   0.01694   0.00801  -0.0418   0.9365   0.1474
  -4.500  -0.3378   0.01528   0.00732  -0.0425   0.9261   0.3235
  -4.250  -0.3094   0.01467   0.00720  -0.0429   0.9182   0.4551
  -4.000  -0.2827   0.01455   0.00718  -0.0425   0.9079   0.5192
  -3.750  -0.2550   0.01457   0.00725  -0.0420   0.8990   0.5708
  -3.500  -0.2280   0.01467   0.00737  -0.0413   0.8902   0.6075
  -3.250  -0.2018   0.01478   0.00742  -0.0405   0.8807   0.6336
  -3.000  -0.1738   0.01486   0.00742  -0.0399   0.8730   0.6539
  -2.750  -0.1478   0.01489   0.00738  -0.0393   0.8630   0.6686
  -2.500  -0.1200   0.01487   0.00725  -0.0390   0.8551   0.6804
  -2.250  -0.0930   0.01484   0.00711  -0.0387   0.8459   0.6921
  -2.000  -0.0663   0.01483   0.00704  -0.0381   0.8376   0.7011
  -1.750  -0.0392   0.01479   0.00692  -0.0378   0.8291   0.7108
  -1.500  -0.0124   0.01477   0.00683  -0.0375   0.8208   0.7203
  -1.250   0.0143   0.01474   0.00676  -0.0370   0.8127   0.7287
  -1.000   0.0412   0.01472   0.00667  -0.0368   0.8041   0.7388
  -0.750   0.0676   0.01471   0.00663  -0.0362   0.7965   0.7465
  -0.500   0.0941   0.01471   0.00660  -0.0359   0.7878   0.7560
  -0.250   0.1206   0.01470   0.00656  -0.0354   0.7805   0.7645
   0.000   0.1466   0.01471   0.00657  -0.0349   0.7718   0.7736
   0.250   0.1734   0.01471   0.00654  -0.0345   0.7647   0.7831
   0.500   0.1989   0.01474   0.00660  -0.0339   0.7559   0.7918
   0.750   0.2257   0.01474   0.00658  -0.0336   0.7489   0.8019
   1.000   0.2509   0.01479   0.00667  -0.0329   0.7402   0.8109
   1.250   0.2773   0.01479   0.00668  -0.0324   0.7332   0.8206
   1.500   0.3030   0.01486   0.00679  -0.0320   0.7244   0.8314
   1.750   0.3288   0.01486   0.00682  -0.0312   0.7175   0.8407
   2.000   0.3538   0.01493   0.00696  -0.0306   0.7084   0.8514
   2.250   0.3801   0.01494   0.00700  -0.0300   0.7015   0.8628
   2.500   0.4046   0.01500   0.00716  -0.0293   0.6919   0.8738
   2.750   0.4304   0.01501   0.00722  -0.0286   0.6841   0.8852
   3.000   0.4559   0.01505   0.00737  -0.0280   0.6745   0.8977
   3.250   0.4823   0.01508   0.00748  -0.0276   0.6651   0.9108
   3.500   0.5105   0.01506   0.00752  -0.0273   0.6558   0.9243
   3.750   0.5396   0.01507   0.00767  -0.0275   0.6434   0.9385
   4.000   0.5718   0.01503   0.00770  -0.0282   0.6284   0.9525
   4.250   0.6067   0.01492   0.00765  -0.0294   0.6097   0.9670
   4.750   0.6682   0.01486   0.00767  -0.0306   0.5535   1.0000
   5.000   0.6898   0.01496   0.00768  -0.0294   0.5164   1.0000
   5.250   0.7115   0.01518   0.00780  -0.0284   0.4668   1.0000
   5.500   0.7320   0.01562   0.00798  -0.0273   0.3991   1.0000
   5.750   0.7479   0.01658   0.00838  -0.0258   0.2972   1.0000
   6.000   0.7606   0.01808   0.00921  -0.0244   0.1910   1.0000
   6.250   0.7756   0.01950   0.01019  -0.0232   0.1230   1.0000
   6.500   0.7923   0.02073   0.01118  -0.0222   0.0895   1.0000
   6.750   0.8101   0.02184   0.01218  -0.0212   0.0733   1.0000
   7.000   0.8277   0.02292   0.01324  -0.0202   0.0633   1.0000
   7.250   0.8462   0.02389   0.01429  -0.0192   0.0564   1.0000
   7.500   0.8621   0.02508   0.01547  -0.0180   0.0519   1.0000
   7.750   0.8798   0.02616   0.01664  -0.0169   0.0480   1.0000
   8.000   0.8973   0.02725   0.01777  -0.0159   0.0442   1.0000
   8.250   0.9132   0.02860   0.01910  -0.0148   0.0418   1.0000
   8.500   0.9318   0.03003   0.02061  -0.0139   0.0402   1.0000
   8.750   0.9525   0.03145   0.02217  -0.0132   0.0383   1.0000
   9.000   0.9728   0.03287   0.02371  -0.0125   0.0363   1.0000
   9.250   0.9914   0.03425   0.02517  -0.0118   0.0344   1.0000
   9.500   1.0101   0.03591   0.02686  -0.0113   0.0330   1.0000
   9.750   1.0311   0.03816   0.02922  -0.0109   0.0320   1.0000
  10.000   1.0492   0.04027   0.03164  -0.0102   0.0313   1.0000
  10.250   1.0642   0.04265   0.03433  -0.0092   0.0307   1.0000
  10.500   1.0751   0.04521   0.03723  -0.0080   0.0302   1.0000
  10.750   1.0805   0.04791   0.04026  -0.0063   0.0298   1.0000
  11.000   1.0809   0.05064   0.04330  -0.0044   0.0294   1.0000
  11.250   1.0772   0.05346   0.04641  -0.0026   0.0290   1.0000
  11.500   1.0704   0.05646   0.04970  -0.0012   0.0285   1.0000
  11.750   1.0611   0.05973   0.05323  -0.0002   0.0282   1.0000
  12.000   1.0497   0.06335   0.05709   0.0001   0.0279   1.0000
  12.250   1.0355   0.06751   0.06149  -0.0003   0.0277   1.0000
  12.500   1.0185   0.07228   0.06649  -0.0015   0.0275   1.0000
  12.750   0.9982   0.07789   0.07232  -0.0038   0.0274   1.0000
  13.000   0.9711   0.08520   0.07988  -0.0077   0.0276   1.0000
  13.250   0.9333   0.09556   0.09047  -0.0142   0.0284   1.0000
  13.500   0.8914   0.10905   0.10415  -0.0235   0.0293   1.0000
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