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NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-412 AIRFOIL (n63412-il)
Reynolds number: 50,000
Max Cl/Cd: 36.11 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63412-il-50000.txt
Download as CSV file: xf-n63412-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-412 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4004   0.11259   0.10539  -0.0196   1.0000   0.3068
  -9.500  -0.3910   0.10923   0.10205  -0.0192   1.0000   0.3213
  -9.250  -0.3819   0.10592   0.09876  -0.0187   1.0000   0.3356
  -9.000  -0.3718   0.10241   0.09527  -0.0184   1.0000   0.3477
  -8.750  -0.3679   0.09935   0.09227  -0.0181   1.0000   0.3588
  -8.500  -0.3706   0.09697   0.08997  -0.0178   1.0000   0.3708
  -8.250  -0.3793   0.09537   0.08849  -0.0170   1.0000   0.3839
  -8.000  -0.3581   0.09055   0.08364  -0.0171   1.0000   0.3884
  -7.750  -0.3701   0.08883   0.08205  -0.0161   1.0000   0.3997
  -7.500  -0.5427   0.06726   0.06088  -0.0462   1.0000   0.1711
  -7.250  -0.5587   0.06161   0.05505  -0.0469   1.0000   0.1553
  -7.000  -0.5717   0.05627   0.04931  -0.0474   1.0000   0.1445
  -6.750  -0.5682   0.05262   0.04537  -0.0466   1.0000   0.1402
  -6.500  -0.5622   0.04904   0.04152  -0.0459   1.0000   0.1383
  -6.250  -0.5529   0.04549   0.03757  -0.0454   1.0000   0.1364
  -6.000  -0.5393   0.04198   0.03354  -0.0452   1.0000   0.1336
  -5.750  -0.5219   0.03885   0.02983  -0.0449   1.0000   0.1316
  -5.500  -0.5028   0.03639   0.02700  -0.0443   1.0000   0.1330
  -5.250  -0.4828   0.03440   0.02468  -0.0437   1.0000   0.1376
  -5.000  -0.4606   0.03255   0.02233  -0.0431   1.0000   0.1417
  -4.750  -0.4389   0.03067   0.02029  -0.0422   1.0000   0.1458
  -4.500  -0.4172   0.02935   0.01884  -0.0413   1.0000   0.1552
  -4.250  -0.3964   0.02803   0.01757  -0.0401   1.0000   0.1663
  -4.000  -0.3761   0.02686   0.01644  -0.0386   1.0000   0.1798
  -3.750  -0.3561   0.02571   0.01541  -0.0374   1.0000   0.2049
  -3.500  -0.3350   0.02403   0.01421  -0.0369   1.0000   0.2593
  -3.250  -0.3326   0.02274   0.01536  -0.0296   1.0000   0.6237
  -3.000  -0.3356   0.02386   0.01652  -0.0210   1.0000   0.6995
  -2.750  -0.3369   0.02456   0.01720  -0.0134   1.0000   0.7472
  -2.500  -0.3386   0.02499   0.01758  -0.0061   1.0000   0.7873
  -2.250  -0.3403   0.02517   0.01771   0.0008   1.0000   0.8280
  -2.000  -0.3452   0.02514   0.01763   0.0088   1.0000   0.8734
  -1.750  -0.2342   0.02662   0.01858  -0.0006   1.0000   0.9666
  -1.500  -0.1356   0.02694   0.01839  -0.0160   1.0000   0.9944
  -1.250  -0.1265   0.02664   0.01798  -0.0163   1.0000   1.0000
  -1.000  -0.1370   0.02612   0.01742  -0.0133   1.0000   1.0000
  -0.750  -0.1468   0.02554   0.01680  -0.0103   1.0000   1.0000
  -0.500  -0.1516   0.02503   0.01621  -0.0080   1.0000   1.0000
  -0.250  -0.1215   0.02544   0.01641  -0.0117   0.9929   1.0000
   0.000  -0.0799   0.02625   0.01700  -0.0172   0.9833   1.0000
   0.250  -0.0438   0.02689   0.01747  -0.0213   0.9740   1.0000
   0.500  -0.0054   0.02772   0.01811  -0.0257   0.9647   1.0000
   0.750   0.0393   0.02881   0.01904  -0.0310   0.9557   1.0000
   1.000   0.0693   0.02949   0.01959  -0.0335   0.9462   1.0000
   1.250   0.1065   0.03047   0.02046  -0.0372   0.9372   1.0000
   1.500   0.1421   0.03144   0.02133  -0.0405   0.9281   1.0000
   1.750   0.1718   0.03234   0.02216  -0.0426   0.9188   1.0000
   2.000   0.2122   0.03352   0.02328  -0.0464   0.9096   1.0000
   2.250   0.2362   0.03437   0.02410  -0.0476   0.8997   1.0000
   2.500   0.2666   0.03544   0.02514  -0.0496   0.8900   1.0000
   2.750   0.3044   0.03662   0.02632  -0.0527   0.8803   1.0000
   3.000   0.3247   0.03758   0.02728  -0.0532   0.8697   1.0000
   3.250   0.3538   0.03872   0.02847  -0.0548   0.8595   1.0000
   3.500   0.3930   0.03996   0.02974  -0.0578   0.8486   1.0000
   3.750   0.4113   0.04101   0.03085  -0.0579   0.8371   1.0000
   4.000   0.4356   0.04219   0.03208  -0.0587   0.8250   1.0000
   4.250   0.4640   0.04338   0.03338  -0.0600   0.8126   1.0000
   4.500   0.4948   0.04457   0.03467  -0.0614   0.7995   1.0000
   4.750   0.5264   0.04571   0.03593  -0.0628   0.7855   1.0000
   5.000   0.5560   0.04681   0.03719  -0.0638   0.7705   1.0000
   5.250   0.5820   0.04789   0.03841  -0.0643   0.7542   1.0000
   5.500   0.6072   0.04894   0.03960  -0.0645   0.7367   1.0000
   5.750   0.6365   0.04981   0.04066  -0.0648   0.7180   1.0000
   6.000   0.6808   0.05001   0.04115  -0.0659   0.6980   1.0000
   6.250   0.7088   0.05048   0.04184  -0.0653   0.6757   1.0000
   6.500   0.7810   0.04793   0.03979  -0.0661   0.6501   1.0000
   6.750   0.8531   0.04301   0.03539  -0.0640   0.6163   1.0000
   7.000   0.9637   0.03062   0.02363  -0.0580   0.5556   1.0000
   7.250   0.9839   0.02725   0.02023  -0.0508   0.4659   1.0000
   7.500   0.9705   0.02825   0.01974  -0.0425   0.2987   1.0000
   7.750   0.9648   0.03147   0.02185  -0.0382   0.2228   1.0000
   8.000   0.9817   0.03418   0.02405  -0.0366   0.1796   1.0000
   8.250   1.0174   0.03673   0.02635  -0.0369   0.1512   1.0000
   8.500   1.0649   0.03990   0.02918  -0.0388   0.1330   1.0000
   8.750   1.0909   0.04240   0.03207  -0.0382   0.1232   1.0000
   9.000   1.1228   0.04600   0.03580  -0.0386   0.1175   1.0000
   9.250   1.1390   0.04906   0.03939  -0.0372   0.1134   1.0000
   9.500   1.1566   0.05223   0.04283  -0.0363   0.1090   1.0000
   9.750   1.1763   0.05619   0.04697  -0.0358   0.1066   1.0000
  10.000   1.1859   0.06035   0.05156  -0.0343   0.1063   1.0000
  10.250   1.1818   0.06424   0.05602  -0.0318   0.1070   1.0000
  10.500   1.1650   0.06834   0.06070  -0.0288   0.1085   1.0000
  10.750   1.1427   0.07273   0.06552  -0.0261   0.1102   1.0000
  11.000   1.1155   0.07700   0.07005  -0.0237   0.1117   1.0000
  11.250   1.0851   0.08189   0.07517  -0.0228   0.1133   1.0000
  11.500   1.0556   0.08759   0.08104  -0.0235   0.1150   1.0000
  11.750   1.0303   0.09408   0.08764  -0.0254   0.1167   1.0000
  12.000   1.0207   0.10056   0.09418  -0.0272   0.1184   1.0000
  12.250   0.7231   0.13006   0.12406  -0.0454   0.1538   1.0000
  12.500   0.7332   0.13543   0.12948  -0.0461   0.1607   1.0000
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