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NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012-34 (naca001234-il)
Reynolds number: 1,000,000
Max Cl/Cd: 56.42 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001234-il-1000000.txt
Download as CSV file: xf-naca001234-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.8163   0.05080   0.04838  -0.0459   1.0000   0.0073
 -10.750  -0.8417   0.04705   0.04446  -0.0425   1.0000   0.0071
 -10.500  -0.8663   0.04384   0.04106  -0.0372   1.0000   0.0070
 -10.250  -0.8898   0.04115   0.03819  -0.0303   1.0000   0.0068
 -10.000  -0.9122   0.03777   0.03455  -0.0232   1.0000   0.0066
  -9.750  -0.9343   0.03419   0.03066  -0.0155   1.0000   0.0064
  -9.500  -0.9487   0.03100   0.02715  -0.0086   1.0000   0.0064
  -9.250  -0.9435   0.02828   0.02414  -0.0054   0.9993   0.0065
  -9.000  -0.9253   0.02511   0.02061  -0.0047   0.9978   0.0067
  -8.750  -0.9032   0.02254   0.01773  -0.0044   0.9964   0.0069
  -8.500  -0.8768   0.02096   0.01594  -0.0048   0.9953   0.0072
  -8.250  -0.8476   0.02000   0.01485  -0.0057   0.9944   0.0075
  -8.000  -0.8238   0.01825   0.01289  -0.0055   0.9927   0.0078
  -7.750  -0.8019   0.01638   0.01088  -0.0051   0.9905   0.0083
  -7.500  -0.7745   0.01552   0.00997  -0.0056   0.9885   0.0087
  -7.250  -0.7452   0.01482   0.00923  -0.0065   0.9869   0.0091
  -7.000  -0.7151   0.01414   0.00850  -0.0076   0.9855   0.0096
  -6.750  -0.6838   0.01357   0.00788  -0.0088   0.9845   0.0104
  -6.500  -0.6509   0.01316   0.00742  -0.0104   0.9836   0.0111
  -6.250  -0.6233   0.01228   0.00645  -0.0108   0.9818   0.0120
  -6.000  -0.5993   0.01157   0.00567  -0.0104   0.9777   0.0132
  -5.750  -0.5699   0.01116   0.00523  -0.0111   0.9751   0.0144
  -5.500  -0.5394   0.01078   0.00481  -0.0120   0.9728   0.0159
  -5.250  -0.5095   0.01040   0.00439  -0.0127   0.9706   0.0175
  -5.000  -0.4853   0.01000   0.00397  -0.0121   0.9659   0.0216
  -4.750  -0.4595   0.00970   0.00364  -0.0118   0.9612   0.0263
  -4.500  -0.4343   0.00926   0.00328  -0.0115   0.9572   0.0458
  -4.250  -0.4164   0.00843   0.00286  -0.0098   0.9509   0.1414
  -4.000  -0.3999   0.00749   0.00247  -0.0080   0.9445   0.2738
  -3.750  -0.3800   0.00687   0.00221  -0.0067   0.9387   0.3685
  -3.500  -0.3584   0.00643   0.00201  -0.0057   0.9322   0.4359
  -3.250  -0.3361   0.00601   0.00182  -0.0047   0.9267   0.5053
  -3.000  -0.3153   0.00560   0.00167  -0.0034   0.9194   0.5791
  -2.750  -0.2928   0.00528   0.00155  -0.0023   0.9134   0.6426
  -2.500  -0.2689   0.00510   0.00148  -0.0016   0.9058   0.6796
  -2.250  -0.2438   0.00496   0.00140  -0.0010   0.8993   0.7160
  -2.000  -0.2180   0.00486   0.00136  -0.0006   0.8916   0.7358
  -1.750  -0.1909   0.00481   0.00130  -0.0005   0.8851   0.7503
  -1.500  -0.1639   0.00476   0.00126  -0.0003   0.8774   0.7632
  -1.250  -0.1367   0.00472   0.00121  -0.0002   0.8706   0.7763
  -1.000  -0.1096   0.00469   0.00119  -0.0001   0.8626   0.7894
  -0.750  -0.0823   0.00467   0.00117  -0.0001   0.8553   0.8013
  -0.500  -0.0550   0.00465   0.00116   0.0000   0.8470   0.8117
  -0.250  -0.0275   0.00464   0.00115   0.0000   0.8389   0.8210
   0.000   0.0000   0.00464   0.00114   0.0000   0.8303   0.8303
   0.250   0.0275   0.00464   0.00115   0.0000   0.8210   0.8389
   0.500   0.0550   0.00465   0.00116   0.0000   0.8117   0.8469
   0.750   0.0822   0.00467   0.00117   0.0001   0.8013   0.8553
   1.000   0.1096   0.00469   0.00119   0.0001   0.7894   0.8626
   1.250   0.1366   0.00472   0.00121   0.0003   0.7764   0.8706
   1.500   0.1639   0.00476   0.00126   0.0003   0.7633   0.8774
   1.750   0.1908   0.00481   0.00130   0.0005   0.7502   0.8851
   2.000   0.2180   0.00486   0.00136   0.0006   0.7359   0.8916
   2.250   0.2437   0.00496   0.00140   0.0010   0.7154   0.8994
   2.500   0.2687   0.00510   0.00148   0.0016   0.6785   0.9058
   2.750   0.2928   0.00528   0.00155   0.0023   0.6425   0.9134
   3.000   0.3154   0.00559   0.00167   0.0034   0.5798   0.9194
   3.250   0.3359   0.00602   0.00182   0.0047   0.5041   0.9268
   3.500   0.3584   0.00643   0.00201   0.0057   0.4362   0.9322
   3.750   0.3799   0.00687   0.00221   0.0067   0.3684   0.9387
   4.000   0.3999   0.00749   0.00247   0.0080   0.2739   0.9445
   4.250   0.4164   0.00843   0.00286   0.0098   0.1415   0.9509
   4.500   0.4343   0.00926   0.00328   0.0115   0.0458   0.9572
   4.750   0.4595   0.00969   0.00363   0.0118   0.0266   0.9612
   5.000   0.4853   0.00999   0.00397   0.0121   0.0216   0.9659
   5.250   0.5096   0.01040   0.00438   0.0127   0.0175   0.9706
   5.500   0.5395   0.01078   0.00481   0.0120   0.0159   0.9729
   5.750   0.5700   0.01115   0.00523   0.0111   0.0144   0.9751
   6.000   0.5994   0.01157   0.00567   0.0104   0.0132   0.9778
   6.250   0.6235   0.01227   0.00643   0.0108   0.0120   0.9818
   6.500   0.6510   0.01317   0.00743   0.0103   0.0111   0.9836
   6.750   0.6840   0.01356   0.00786   0.0088   0.0104   0.9845
   7.000   0.7153   0.01414   0.00850   0.0075   0.0096   0.9856
   7.250   0.7453   0.01482   0.00923   0.0065   0.0091   0.9869
   7.500   0.7746   0.01551   0.00996   0.0056   0.0087   0.9885
   7.750   0.8020   0.01638   0.01088   0.0050   0.0083   0.9905
   8.000   0.8240   0.01825   0.01289   0.0055   0.0078   0.9927
   8.250   0.8478   0.02003   0.01488   0.0057   0.0075   0.9944
   8.500   0.8771   0.02093   0.01591   0.0047   0.0072   0.9953
   8.750   0.9035   0.02254   0.01773   0.0043   0.0069   0.9964
   9.000   0.9256   0.02512   0.02062   0.0046   0.0067   0.9978
   9.250   0.9442   0.02822   0.02407   0.0053   0.0065   0.9993
   9.500   0.9478   0.03112   0.02729   0.0088   0.0064   1.0000
   9.750   0.9345   0.03416   0.03063   0.0155   0.0064   1.0000
  10.000   0.9116   0.03785   0.03464   0.0234   0.0066   1.0000
  10.250   0.8894   0.04120   0.03824   0.0304   0.0068   1.0000
  10.500   0.8661   0.04389   0.04111   0.0372   0.0070   1.0000
  10.750   0.8422   0.04706   0.04447   0.0424   0.0071   1.0000
  11.000   0.8141   0.05101   0.04860   0.0459   0.0073   1.0000
  11.250   0.7097   0.04360   0.04134   0.0525   0.0076   1.0000
  11.500   0.6878   0.04814   0.04602   0.0526   0.0075   1.0000
  11.750   0.6654   0.05353   0.05152   0.0515   0.0075   1.0000
  12.000   0.6424   0.05978   0.05789   0.0492   0.0075   1.0000
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