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NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012-34 (naca001234-il)
Reynolds number: 500,000
Max Cl/Cd: 45.56 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001234-il-500000-n5.txt
Download as CSV file: xf-naca001234-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8029   0.06148   0.05877  -0.0435   1.0000   0.0034
 -12.000  -0.8242   0.05564   0.05274  -0.0456   1.0000   0.0034
 -11.750  -0.8456   0.05056   0.04744  -0.0458   1.0000   0.0034
 -11.500  -0.8652   0.04623   0.04287  -0.0446   1.0000   0.0034
 -11.250  -0.8836   0.04241   0.03879  -0.0420   1.0000   0.0034
 -11.000  -0.9016   0.03892   0.03502  -0.0383   1.0000   0.0035
 -10.750  -0.9116   0.03656   0.03245  -0.0344   1.0000   0.0036
 -10.500  -0.9177   0.03488   0.03061  -0.0301   1.0000   0.0036
 -10.250  -0.9204   0.03391   0.02954  -0.0257   1.0000   0.0037
 -10.000  -0.9197   0.03276   0.02826  -0.0219   1.0000   0.0038
  -9.750  -0.9173   0.03176   0.02713  -0.0181   1.0000   0.0039
  -9.500  -0.9145   0.03069   0.02592  -0.0143   1.0000   0.0040
  -9.250  -0.9120   0.02935   0.02441  -0.0103   1.0000   0.0042
  -9.000  -0.8976   0.02743   0.02224  -0.0088   0.9987   0.0044
  -8.750  -0.8766   0.02509   0.01959  -0.0084   0.9967   0.0045
  -8.500  -0.8533   0.02313   0.01735  -0.0083   0.9951   0.0047
  -8.250  -0.8298   0.02152   0.01553  -0.0082   0.9929   0.0050
  -8.000  -0.8053   0.02019   0.01401  -0.0081   0.9906   0.0052
  -7.750  -0.7790   0.01911   0.01278  -0.0084   0.9885   0.0054
  -7.500  -0.7546   0.01769   0.01123  -0.0086   0.9867   0.0057
  -7.250  -0.7296   0.01687   0.01032  -0.0087   0.9838   0.0061
  -7.000  -0.7023   0.01630   0.00971  -0.0092   0.9810   0.0067
  -6.750  -0.6736   0.01570   0.00905  -0.0099   0.9789   0.0074
  -6.500  -0.6450   0.01502   0.00828  -0.0106   0.9770   0.0080
  -6.250  -0.6201   0.01437   0.00755  -0.0104   0.9732   0.0085
  -6.000  -0.5965   0.01352   0.00660  -0.0100   0.9691   0.0097
  -5.750  -0.5681   0.01304   0.00608  -0.0105   0.9664   0.0111
  -5.500  -0.5406   0.01266   0.00563  -0.0109   0.9631   0.0129
  -5.250  -0.5159   0.01226   0.00515  -0.0104   0.9579   0.0148
  -5.000  -0.4889   0.01182   0.00468  -0.0105   0.9541   0.0211
  -4.750  -0.4618   0.01144   0.00432  -0.0106   0.9504   0.0331
  -4.250  -0.4171   0.01023   0.00354  -0.0092   0.9393   0.1385
  -4.000  -0.3981   0.00942   0.00316  -0.0080   0.9331   0.2434
  -3.750  -0.3796   0.00859   0.00282  -0.0066   0.9267   0.3614
  -3.500  -0.3602   0.00794   0.00256  -0.0053   0.9206   0.4588
  -3.250  -0.3399   0.00746   0.00236  -0.0039   0.9137   0.5349
  -3.000  -0.3172   0.00711   0.00220  -0.0030   0.9079   0.5924
  -2.750  -0.2942   0.00687   0.00210  -0.0020   0.9008   0.6384
  -2.500  -0.2683   0.00671   0.00198  -0.0017   0.8950   0.6670
  -2.250  -0.2425   0.00661   0.00190  -0.0013   0.8874   0.6865
  -2.000  -0.2157   0.00651   0.00181  -0.0011   0.8809   0.7056
  -1.750  -0.1896   0.00643   0.00174  -0.0008   0.8726   0.7249
  -1.500  -0.1629   0.00636   0.00168  -0.0006   0.8646   0.7419
  -1.250  -0.1360   0.00631   0.00163  -0.0004   0.8560   0.7563
  -1.000  -0.1090   0.00627   0.00159  -0.0003   0.8473   0.7692
  -0.750  -0.0818   0.00624   0.00156  -0.0002   0.8391   0.7808
  -0.500  -0.0546   0.00622   0.00154  -0.0001   0.8300   0.7916
  -0.250  -0.0273   0.00621   0.00152  -0.0001   0.8211   0.8019
   0.000   0.0000   0.00621   0.00151   0.0000   0.8120   0.8120
   0.250   0.0273   0.00621   0.00152   0.0001   0.8019   0.8211
   0.500   0.0546   0.00622   0.00154   0.0001   0.7916   0.8300
   0.750   0.0818   0.00624   0.00156   0.0002   0.7809   0.8391
   1.000   0.1091   0.00627   0.00159   0.0003   0.7693   0.8473
   1.250   0.1360   0.00631   0.00163   0.0004   0.7563   0.8560
   1.500   0.1629   0.00636   0.00168   0.0006   0.7419   0.8646
   1.750   0.1896   0.00643   0.00174   0.0008   0.7249   0.8726
   2.000   0.2157   0.00651   0.00181   0.0011   0.7055   0.8808
   2.250   0.2425   0.00661   0.00190   0.0013   0.6865   0.8874
   2.500   0.2683   0.00671   0.00198   0.0017   0.6672   0.8950
   2.750   0.2942   0.00687   0.00210   0.0020   0.6382   0.9007
   3.000   0.3172   0.00712   0.00220   0.0030   0.5922   0.9079
   3.250   0.3399   0.00746   0.00236   0.0039   0.5347   0.9137
   3.500   0.3603   0.00794   0.00256   0.0052   0.4590   0.9205
   3.750   0.3797   0.00859   0.00282   0.0066   0.3616   0.9267
   4.000   0.3981   0.00942   0.00316   0.0080   0.2425   0.9330
   4.250   0.4171   0.01023   0.00354   0.0092   0.1379   0.9393
   4.750   0.4619   0.01143   0.00432   0.0106   0.0330   0.9504
   5.000   0.4889   0.01182   0.00468   0.0105   0.0211   0.9540
   5.250   0.5160   0.01225   0.00514   0.0104   0.0149   0.9578
   5.500   0.5408   0.01266   0.00563   0.0108   0.0129   0.9630
   5.750   0.5682   0.01304   0.00607   0.0105   0.0111   0.9663
   6.000   0.5966   0.01352   0.00660   0.0100   0.0097   0.9691
   6.250   0.6201   0.01439   0.00757   0.0104   0.0085   0.9733
   6.500   0.6451   0.01502   0.00828   0.0106   0.0080   0.9770
   6.750   0.6738   0.01570   0.00905   0.0099   0.0074   0.9789
   7.000   0.7026   0.01628   0.00969   0.0091   0.0066   0.9810
   7.250   0.7297   0.01687   0.01032   0.0086   0.0061   0.9839
   7.500   0.7549   0.01769   0.01123   0.0085   0.0057   0.9867
   7.750   0.7792   0.01912   0.01279   0.0084   0.0054   0.9886
   8.000   0.8055   0.02020   0.01402   0.0081   0.0052   0.9906
   8.250   0.8301   0.02152   0.01553   0.0081   0.0050   0.9930
   8.500   0.8536   0.02313   0.01735   0.0083   0.0047   0.9951
   8.750   0.8770   0.02510   0.01959   0.0083   0.0045   0.9967
   9.000   0.8979   0.02745   0.02226   0.0087   0.0044   0.9987
   9.250   0.9117   0.02939   0.02446   0.0104   0.0042   1.0000
   9.500   0.9147   0.03063   0.02586   0.0143   0.0040   1.0000
   9.750   0.9175   0.03172   0.02709   0.0181   0.0039   1.0000
  10.000   0.9190   0.03289   0.02841   0.0220   0.0038   1.0000
  10.250   0.9201   0.03399   0.02963   0.0258   0.0037   1.0000
  10.500   0.9179   0.03492   0.03065   0.0301   0.0036   1.0000
  10.750   0.9123   0.03655   0.03244   0.0343   0.0036   1.0000
  11.000   0.9017   0.03899   0.03510   0.0382   0.0035   1.0000
  11.250   0.8849   0.04238   0.03876   0.0419   0.0034   1.0000
  11.500   0.8658   0.04627   0.04291   0.0445   0.0034   1.0000
  11.750   0.8459   0.05065   0.04753   0.0457   0.0034   1.0000
  12.000   0.8246   0.05573   0.05283   0.0454   0.0034   1.0000
  12.500   0.7833   0.06857   0.06605   0.0393   0.0035   1.0000
  12.750   0.7451   0.08192   0.07965   0.0305   0.0036   1.0000
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