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NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012-34 (naca001234-il)
Reynolds number: 100,000
Max Cl/Cd: 36.72 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001234-il-100000-n5.txt
Download as CSV file: xf-naca001234-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-34                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6411   0.08921   0.08427  -0.0362   1.0000   0.0199
 -11.000  -0.6607   0.08149   0.07649  -0.0414   1.0000   0.0195
 -10.750  -0.6820   0.07531   0.07020  -0.0446   1.0000   0.0191
 -10.500  -0.7031   0.07030   0.06506  -0.0458   1.0000   0.0188
 -10.250  -0.7230   0.06622   0.06083  -0.0452   1.0000   0.0187
 -10.000  -0.7420   0.06276   0.05721  -0.0431   1.0000   0.0185
  -9.750  -0.7600   0.05983   0.05411  -0.0395   1.0000   0.0185
  -9.500  -0.7756   0.05706   0.05115  -0.0353   1.0000   0.0185
  -9.250  -0.7869   0.05416   0.04801  -0.0312   1.0000   0.0185
  -9.000  -0.7955   0.05127   0.04485  -0.0270   1.0000   0.0185
  -8.750  -0.8013   0.04838   0.04166  -0.0227   1.0000   0.0184
  -8.500  -0.8038   0.04554   0.03849  -0.0186   1.0000   0.0184
  -8.250  -0.8031   0.04281   0.03540  -0.0146   1.0000   0.0184
  -8.000  -0.7991   0.04019   0.03242  -0.0109   1.0000   0.0185
  -7.750  -0.7916   0.03769   0.02956  -0.0076   1.0000   0.0187
  -7.500  -0.7805   0.03534   0.02685  -0.0047   1.0000   0.0191
  -7.250  -0.7665   0.03323   0.02434  -0.0022   1.0000   0.0198
  -7.000  -0.7506   0.03147   0.02229   0.0000   1.0000   0.0214
  -6.750  -0.7323   0.02979   0.02033   0.0019   1.0000   0.0228
  -6.500  -0.7129   0.02814   0.01847   0.0036   1.0000   0.0237
  -6.250  -0.6950   0.02675   0.01692   0.0055   1.0000   0.0246
  -6.000  -0.6820   0.02518   0.01534   0.0080   1.0000   0.0262
  -5.750  -0.6698   0.02417   0.01433   0.0105   1.0000   0.0291
  -5.500  -0.6573   0.02325   0.01330   0.0132   1.0000   0.0322
  -5.250  -0.6449   0.02237   0.01226   0.0159   1.0000   0.0347
  -5.000  -0.6327   0.02142   0.01121   0.0185   1.0000   0.0402
  -4.750  -0.6186   0.02056   0.01029   0.0208   1.0000   0.0495
  -4.500  -0.6043   0.01958   0.00940   0.0231   1.0000   0.0733
  -4.250  -0.5972   0.01752   0.00850   0.0258   1.0000   0.2575
  -4.000  -0.5828   0.01587   0.00813   0.0276   0.9973   0.4949
  -3.750  -0.5591   0.01537   0.00845   0.0292   0.9940   0.6666
  -3.500  -0.5310   0.01563   0.00890   0.0305   0.9900   0.7561
  -3.250  -0.4964   0.01587   0.00898   0.0295   0.9865   0.7857
  -3.000  -0.4626   0.01604   0.00898   0.0284   0.9821   0.8050
  -2.750  -0.4273   0.01622   0.00896   0.0269   0.9781   0.8232
  -2.500  -0.3926   0.01639   0.00897   0.0255   0.9738   0.8389
  -2.250  -0.3574   0.01656   0.00899   0.0239   0.9691   0.8521
  -2.000  -0.3178   0.01675   0.00903   0.0214   0.9657   0.8631
  -1.750  -0.2826   0.01690   0.00906   0.0198   0.9605   0.8736
  -1.500  -0.2459   0.01702   0.00907   0.0178   0.9556   0.8839
  -1.250  -0.2034   0.01717   0.00911   0.0145   0.9523   0.8920
  -1.000  -0.1670   0.01728   0.00915   0.0126   0.9465   0.9001
  -0.750  -0.1289   0.01735   0.00915   0.0102   0.9413   0.9090
  -0.250  -0.0453   0.01750   0.00923   0.0039   0.9314   0.9218
   0.000   0.0000   0.01751   0.00923   0.0000   0.9268   0.9268
   0.250   0.0453   0.01749   0.00923  -0.0039   0.9218   0.9314
   0.750   0.1290   0.01734   0.00915  -0.0102   0.9090   0.9413
   1.000   0.1670   0.01728   0.00915  -0.0126   0.9001   0.9465
   1.250   0.2034   0.01716   0.00911  -0.0145   0.8921   0.9524
   1.500   0.2459   0.01701   0.00907  -0.0178   0.8839   0.9556
   1.750   0.2826   0.01690   0.00906  -0.0198   0.8736   0.9606
   2.000   0.3178   0.01675   0.00903  -0.0214   0.8631   0.9657
   2.250   0.3574   0.01655   0.00899  -0.0239   0.8521   0.9691
   2.500   0.3926   0.01638   0.00896  -0.0255   0.8389   0.9738
   2.750   0.4273   0.01622   0.00896  -0.0269   0.8232   0.9781
   3.000   0.4626   0.01604   0.00898  -0.0284   0.8050   0.9822
   3.250   0.4964   0.01587   0.00898  -0.0295   0.7857   0.9866
   3.500   0.5310   0.01563   0.00890  -0.0305   0.7561   0.9901
   3.750   0.5591   0.01536   0.00845  -0.0292   0.6665   0.9940
   4.000   0.5828   0.01587   0.00813  -0.0276   0.4951   0.9974
   4.250   0.5970   0.01752   0.00850  -0.0258   0.2577   1.0000
   4.500   0.6042   0.01957   0.00939  -0.0231   0.0734   1.0000
   4.750   0.6185   0.02055   0.01028  -0.0208   0.0496   1.0000
   5.000   0.6326   0.02141   0.01121  -0.0185   0.0403   1.0000
   5.250   0.6448   0.02236   0.01225  -0.0159   0.0347   1.0000
   5.500   0.6572   0.02325   0.01329  -0.0131   0.0322   1.0000
   5.750   0.6697   0.02417   0.01432  -0.0105   0.0292   1.0000
   6.000   0.6819   0.02517   0.01534  -0.0080   0.0262   1.0000
   6.250   0.6949   0.02674   0.01691  -0.0055   0.0246   1.0000
   6.500   0.7128   0.02813   0.01846  -0.0036   0.0237   1.0000
   6.750   0.7322   0.02978   0.02032  -0.0019   0.0228   1.0000
   7.000   0.7504   0.03146   0.02227   0.0000   0.0214   1.0000
   7.250   0.7664   0.03322   0.02433   0.0022   0.0198   1.0000
   7.500   0.7804   0.03533   0.02683   0.0047   0.0191   1.0000
   7.750   0.7915   0.03768   0.02954   0.0076   0.0187   1.0000
   8.000   0.7990   0.04018   0.03240   0.0109   0.0185   1.0000
   8.250   0.8031   0.04280   0.03539   0.0146   0.0184   1.0000
   8.500   0.8038   0.04554   0.03849   0.0186   0.0184   1.0000
   8.750   0.8013   0.04838   0.04166   0.0227   0.0184   1.0000
   9.000   0.7956   0.05127   0.04485   0.0270   0.0185   1.0000
   9.250   0.7871   0.05416   0.04802   0.0312   0.0185   1.0000
   9.500   0.7758   0.05708   0.05117   0.0352   0.0185   1.0000
   9.750   0.7603   0.05985   0.05413   0.0394   0.0185   1.0000
  10.000   0.7423   0.06278   0.05723   0.0430   0.0185   1.0000
  10.250   0.7234   0.06625   0.06087   0.0451   0.0187   1.0000
  10.500   0.7035   0.07036   0.06512   0.0457   0.0188   1.0000
  10.750   0.6825   0.07538   0.07027   0.0445   0.0191   1.0000
  11.000   0.6613   0.08158   0.07658   0.0412   0.0195   1.0000
  11.250   0.6418   0.08931   0.08438   0.0360   0.0199   1.0000
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