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NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012-34 (naca001234-il)
Reynolds number: 50,000
Max Cl/Cd: 27.51 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001234-il-50000-n5.txt
Download as CSV file: xf-naca001234-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6643   0.09163   0.08449  -0.0416   1.0000   0.0343
 -11.000  -0.6781   0.08662   0.07943  -0.0435   1.0000   0.0341
 -10.750  -0.6931   0.08207   0.07481  -0.0446   1.0000   0.0339
 -10.500  -0.7096   0.07798   0.07062  -0.0446   1.0000   0.0338
 -10.250  -0.7264   0.07437   0.06689  -0.0435   1.0000   0.0337
 -10.000  -0.7432   0.07118   0.06357  -0.0411   1.0000   0.0336
  -9.750  -0.7590   0.06825   0.06046  -0.0379   1.0000   0.0336
  -9.500  -0.7711   0.06518   0.05717  -0.0347   1.0000   0.0336
  -9.250  -0.7802   0.06214   0.05386  -0.0314   1.0000   0.0337
  -9.000  -0.7863   0.05912   0.05054  -0.0279   1.0000   0.0338
  -8.750  -0.7892   0.05612   0.04721  -0.0245   1.0000   0.0339
  -8.500  -0.7887   0.05315   0.04388  -0.0212   1.0000   0.0340
  -8.250  -0.7850   0.05026   0.04060  -0.0179   1.0000   0.0341
  -8.000  -0.7778   0.04748   0.03740  -0.0149   1.0000   0.0344
  -7.750  -0.7658   0.04439   0.03393  -0.0127   1.0000   0.0350
  -7.500  -0.7516   0.04180   0.03118  -0.0110   1.0000   0.0368
  -7.250  -0.7351   0.03970   0.02888  -0.0093   1.0000   0.0394
  -7.000  -0.7138   0.03756   0.02640  -0.0079   1.0000   0.0420
  -6.750  -0.6864   0.03544   0.02395  -0.0071   1.0000   0.0441
  -6.500  -0.6617   0.03334   0.02182  -0.0064   1.0000   0.0479
  -6.250  -0.6431   0.03194   0.02029  -0.0047   1.0000   0.0540
  -6.000  -0.6267   0.03054   0.01868  -0.0024   1.0000   0.0589
  -5.750  -0.6150   0.02917   0.01726   0.0003   1.0000   0.0663
  -5.500  -0.6040   0.02787   0.01586   0.0030   1.0000   0.0801
  -5.250  -0.5945   0.02630   0.01441   0.0060   1.0000   0.1030
  -5.000  -0.5951   0.02361   0.01298   0.0098   1.0000   0.2462
  -4.750  -0.5978   0.02174   0.01255   0.0155   1.0000   0.4871
  -4.500  -0.5832   0.02195   0.01366   0.0214   1.0000   0.6804
  -4.250  -0.5547   0.02370   0.01537   0.0261   1.0000   0.7746
  -4.000  -0.5299   0.02391   0.01523   0.0274   1.0000   0.7993
  -3.750  -0.4966   0.02422   0.01514   0.0271   1.0000   0.8189
  -3.500  -0.4698   0.02434   0.01496   0.0276   1.0000   0.8391
  -3.250  -0.4374   0.02451   0.01482   0.0269   1.0000   0.8561
  -3.000  -0.4027   0.02465   0.01464   0.0256   1.0000   0.8715
  -2.750  -0.3678   0.02474   0.01447   0.0241   1.0000   0.8862
  -2.500  -0.3312   0.02478   0.01427   0.0220   1.0000   0.9000
  -2.250  -0.2946   0.02478   0.01403   0.0197   1.0000   0.9134
  -2.000  -0.2583   0.02475   0.01382   0.0173   1.0000   0.9263
  -1.750  -0.2221   0.02471   0.01362   0.0148   1.0000   0.9390
  -1.500  -0.1859   0.02466   0.01342   0.0122   1.0000   0.9516
  -1.250  -0.1453   0.02459   0.01323   0.0086   1.0000   0.9623
  -1.000  -0.1063   0.02450   0.01304   0.0052   1.0000   0.9733
  -0.750  -0.0670   0.02441   0.01289   0.0016   1.0000   0.9840
  -0.500  -0.0267   0.02432   0.01275  -0.0023   1.0000   0.9942
  -0.250  -0.0012   0.02424   0.01266  -0.0034   1.0000   1.0000
   0.000   0.0000   0.02422   0.01265   0.0000   1.0000   1.0000
   0.250   0.0012   0.02424   0.01266   0.0034   1.0000   1.0000
   0.500   0.0267   0.02431   0.01275   0.0023   0.9942   1.0000
   0.750   0.0669   0.02441   0.01289  -0.0016   0.9840   1.0000
   1.000   0.1063   0.02450   0.01304  -0.0052   0.9733   1.0000
   1.250   0.1452   0.02458   0.01322  -0.0086   0.9623   1.0000
   1.500   0.1858   0.02466   0.01341  -0.0122   0.9516   1.0000
   1.750   0.2220   0.02471   0.01362  -0.0148   0.9390   1.0000
   2.000   0.2582   0.02475   0.01381  -0.0173   0.9264   1.0000
   2.250   0.2945   0.02477   0.01402  -0.0196   0.9134   1.0000
   2.500   0.3312   0.02477   0.01426  -0.0219   0.9001   1.0000
   2.750   0.3678   0.02473   0.01446  -0.0241   0.8863   1.0000
   3.000   0.4026   0.02465   0.01464  -0.0256   0.8715   1.0000
   3.250   0.4373   0.02451   0.01482  -0.0269   0.8561   1.0000
   3.500   0.4698   0.02434   0.01495  -0.0276   0.8391   1.0000
   3.750   0.4965   0.02421   0.01513  -0.0271   0.8189   1.0000
   4.000   0.5298   0.02390   0.01522  -0.0274   0.7993   1.0000
   4.250   0.5547   0.02369   0.01537  -0.0261   0.7746   1.0000
   4.500   0.5831   0.02195   0.01366  -0.0214   0.6804   1.0000
   4.750   0.5978   0.02173   0.01255  -0.0155   0.4874   1.0000
   5.000   0.5951   0.02359   0.01297  -0.0098   0.2474   1.0000
   5.250   0.5945   0.02629   0.01440  -0.0060   0.1031   1.0000
   5.500   0.6040   0.02786   0.01585  -0.0030   0.0802   1.0000
   5.750   0.6150   0.02916   0.01725  -0.0003   0.0664   1.0000
   6.000   0.6266   0.03053   0.01868   0.0024   0.0589   1.0000
   6.250   0.6431   0.03194   0.02028   0.0047   0.0540   1.0000
   6.500   0.6616   0.03334   0.02181   0.0064   0.0479   1.0000
   6.750   0.6864   0.03544   0.02394   0.0071   0.0441   1.0000
   7.000   0.7137   0.03755   0.02639   0.0079   0.0420   1.0000
   7.250   0.7351   0.03970   0.02887   0.0093   0.0394   1.0000
   7.500   0.7516   0.04179   0.03117   0.0110   0.0368   1.0000
   7.750   0.7658   0.04438   0.03392   0.0127   0.0350   1.0000
   8.000   0.7777   0.04748   0.03739   0.0149   0.0344   1.0000
   8.250   0.7850   0.05025   0.04059   0.0179   0.0341   1.0000
   8.500   0.7887   0.05314   0.04387   0.0212   0.0340   1.0000
   8.750   0.7892   0.05612   0.04720   0.0245   0.0339   1.0000
   9.000   0.7864   0.05912   0.05054   0.0279   0.0338   1.0000
   9.250   0.7804   0.06215   0.05387   0.0314   0.0337   1.0000
   9.500   0.7713   0.06519   0.05718   0.0347   0.0336   1.0000
   9.750   0.7593   0.06826   0.06048   0.0378   0.0336   1.0000
  10.000   0.7437   0.07121   0.06359   0.0410   0.0336   1.0000
  10.250   0.7267   0.07439   0.06692   0.0434   0.0337   1.0000
  10.500   0.7099   0.07802   0.07066   0.0445   0.0338   1.0000
  10.750   0.6937   0.08210   0.07484   0.0445   0.0340   1.0000
  11.000   0.6784   0.08668   0.07950   0.0434   0.0341   1.0000
  11.250   0.6649   0.09169   0.08455   0.0415   0.0343   1.0000
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