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NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012-34 (naca001234-il)
Reynolds number: 500,000
Max Cl/Cd: 49.05 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001234-il-500000.txt
Download as CSV file: xf-naca001234-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6728   0.08736   0.08500  -0.0377   1.0000   0.0174
 -11.750  -0.6903   0.08051   0.07803  -0.0432   1.0000   0.0172
 -11.500  -0.7060   0.07554   0.07294  -0.0463   1.0000   0.0171
 -11.250  -0.7255   0.07082   0.06809  -0.0480   1.0000   0.0171
 -11.000  -0.7465   0.06653   0.06368  -0.0481   1.0000   0.0171
 -10.750  -0.7700   0.06231   0.05933  -0.0467   1.0000   0.0172
 -10.500  -0.7914   0.05875   0.05564  -0.0439   1.0000   0.0173
  -7.750  -0.8601   0.02984   0.02462   0.0058   0.9994   0.0144
  -7.500  -0.8386   0.02500   0.01919   0.0072   0.9978   0.0133
  -7.250  -0.8103   0.02289   0.01684   0.0068   0.9963   0.0136
  -7.000  -0.7803   0.02121   0.01497   0.0060   0.9950   0.0140
  -6.750  -0.7499   0.02012   0.01377   0.0051   0.9934   0.0150
  -6.500  -0.7203   0.01914   0.01268   0.0044   0.9910   0.0159
  -6.250  -0.6901   0.01812   0.01153   0.0036   0.9888   0.0165
  -6.000  -0.6631   0.01649   0.00980   0.0033   0.9867   0.0173
  -5.750  -0.6354   0.01517   0.00841   0.0027   0.9846   0.0189
  -5.500  -0.6028   0.01450   0.00771   0.0012   0.9831   0.0207
  -5.250  -0.5754   0.01404   0.00719   0.0010   0.9791   0.0231
  -5.000  -0.5468   0.01331   0.00637   0.0004   0.9757   0.0257
  -4.750  -0.5152   0.01265   0.00568  -0.0007   0.9733   0.0313
  -4.500  -0.4819   0.01201   0.00505  -0.0022   0.9715   0.0487
  -4.250  -0.4589   0.01005   0.00424  -0.0028   0.9696   0.2862
  -4.000  -0.4418   0.00916   0.00389  -0.0011   0.9628   0.4153
  -3.750  -0.4141   0.00843   0.00361  -0.0017   0.9597   0.5224
  -3.500  -0.3843   0.00794   0.00340  -0.0024   0.9573   0.6027
  -3.250  -0.3591   0.00757   0.00331  -0.0018   0.9532   0.6736
  -3.000  -0.3342   0.00737   0.00323  -0.0011   0.9478   0.7176
  -2.750  -0.3047   0.00721   0.00316  -0.0014   0.9444   0.7525
  -2.500  -0.2732   0.00709   0.00306  -0.0021   0.9417   0.7741
  -2.250  -0.2488   0.00703   0.00298  -0.0013   0.9348   0.7878
  -2.000  -0.2195   0.00693   0.00287  -0.0015   0.9304   0.8010
  -1.750  -0.1909   0.00685   0.00279  -0.0016   0.9257   0.8137
  -1.500  -0.1647   0.00679   0.00275  -0.0011   0.9187   0.8254
  -1.250  -0.1354   0.00672   0.00266  -0.0012   0.9140   0.8356
  -1.000  -0.1099   0.00669   0.00263  -0.0007   0.9064   0.8458
  -0.750  -0.0817   0.00664   0.00257  -0.0006   0.9008   0.8551
  -0.500  -0.0548   0.00663   0.00258  -0.0004   0.8934   0.8631
  -0.250  -0.0275   0.00660   0.00252  -0.0002   0.8869   0.8720
   0.000   0.0000   0.00661   0.00255   0.0000   0.8790   0.8791
   0.250   0.0275   0.00660   0.00252   0.0002   0.8720   0.8869
   0.500   0.0548   0.00663   0.00258   0.0004   0.8632   0.8934
   0.750   0.0817   0.00664   0.00257   0.0006   0.8551   0.9008
   1.000   0.1098   0.00669   0.00263   0.0007   0.8458   0.9064
   1.250   0.1354   0.00672   0.00266   0.0013   0.8356   0.9141
   1.500   0.1647   0.00679   0.00275   0.0011   0.8254   0.9187
   1.750   0.1909   0.00685   0.00279   0.0016   0.8137   0.9257
   2.000   0.2195   0.00693   0.00287   0.0015   0.8010   0.9304
   2.250   0.2488   0.00703   0.00298   0.0013   0.7879   0.9348
   2.500   0.2732   0.00709   0.00305   0.0021   0.7741   0.9417
   2.750   0.3047   0.00721   0.00315   0.0014   0.7525   0.9444
   3.000   0.3342   0.00737   0.00322   0.0011   0.7176   0.9478
   3.250   0.3591   0.00757   0.00331   0.0018   0.6737   0.9533
   3.750   0.4140   0.00844   0.00361   0.0017   0.5218   0.9597
   4.000   0.4418   0.00916   0.00389   0.0011   0.4156   0.9628
   4.250   0.4589   0.01005   0.00424   0.0028   0.2857   0.9696
   4.500   0.4819   0.01201   0.00505   0.0022   0.0485   0.9715
   4.750   0.5152   0.01265   0.00567   0.0007   0.0313   0.9733
   5.000   0.5468   0.01331   0.00637  -0.0005   0.0257   0.9757
   5.250   0.5754   0.01404   0.00719  -0.0010   0.0232   0.9791
   5.500   0.6028   0.01450   0.00771  -0.0012   0.0207   0.9831
   5.750   0.6355   0.01517   0.00841  -0.0028   0.0189   0.9846
   6.000   0.6633   0.01648   0.00979  -0.0034   0.0173   0.9867
   6.250   0.6902   0.01812   0.01154  -0.0036   0.0165   0.9888
   6.500   0.7204   0.01914   0.01268  -0.0044   0.0159   0.9911
   6.750   0.7501   0.02007   0.01371  -0.0051   0.0149   0.9934
   7.000   0.7804   0.02120   0.01496  -0.0060   0.0140   0.9950
   7.250   0.8103   0.02289   0.01684  -0.0068   0.0136   0.9963
   7.500   0.8387   0.02499   0.01919  -0.0072   0.0133   0.9978
   7.750   0.8602   0.02987   0.02465  -0.0058   0.0144   0.9994
   8.250   0.8199   0.02873   0.02490   0.0081   0.0206   1.0000
   8.500   0.8139   0.03076   0.02710   0.0131   0.0200   1.0000
   8.750   0.8055   0.03282   0.02931   0.0182   0.0197   1.0000
   9.000   0.7949   0.03485   0.03147   0.0236   0.0193   1.0000
   9.250   0.7824   0.03693   0.03367   0.0290   0.0191   1.0000
   9.500   0.7683   0.03905   0.03591   0.0344   0.0188   1.0000
   9.750   0.7497   0.04099   0.03795   0.0404   0.0187   1.0000
  10.000   0.7290   0.04314   0.04019   0.0458   0.0186   1.0000
  10.250   0.7093   0.04581   0.04297   0.0495   0.0186   1.0000
  10.500   0.6868   0.04913   0.04643   0.0521   0.0185   1.0000
  10.750   0.6617   0.05320   0.05061   0.0534   0.0186   1.0000
  11.000   0.6322   0.05851   0.05606   0.0532   0.0187   1.0000
  11.250   0.5971   0.06574   0.06343   0.0508   0.0190   1.0000
  11.500   0.5526   0.07693   0.07476   0.0445   0.0197   1.0000
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