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NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-012 (naca16012-il)
Reynolds number: 200,000
Max Cl/Cd: 32.51 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16012-il-200000-n5.txt
Download as CSV file: xf-naca16012-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-012                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6765   0.08272   0.07916  -0.0523   1.0000   0.0121
 -11.750  -0.7221   0.07176   0.06805  -0.0566   1.0000   0.0116
 -11.500  -0.7631   0.06495   0.06107  -0.0555   1.0000   0.0114
 -11.250  -0.7978   0.06025   0.05619  -0.0518   1.0000   0.0113
 -11.000  -0.8291   0.05659   0.05235  -0.0465   1.0000   0.0112
 -10.750  -0.8581   0.05364   0.04923  -0.0401   1.0000   0.0112
 -10.500  -0.8857   0.05126   0.04666  -0.0327   1.0000   0.0112
 -10.250  -0.9121   0.04928   0.04451  -0.0247   1.0000   0.0112
 -10.000  -0.9323   0.04693   0.04193  -0.0175   1.0000   0.0113
  -9.750  -0.9467   0.04445   0.03919  -0.0112   1.0000   0.0114
  -9.500  -0.9559   0.04196   0.03641  -0.0055   0.9999   0.0116
  -9.250  -0.9481   0.03865   0.03265  -0.0033   0.9974   0.0120
  -9.000  -0.9359   0.03572   0.02929  -0.0016   0.9954   0.0125
  -8.750  -0.9202   0.03351   0.02670  -0.0001   0.9936   0.0134
  -8.500  -0.9020   0.03162   0.02443   0.0012   0.9916   0.0144
  -8.250  -0.8816   0.02955   0.02199   0.0021   0.9899   0.0152
  -8.000  -0.8599   0.02772   0.01995   0.0025   0.9884   0.0162
  -7.750  -0.8353   0.02667   0.01877   0.0025   0.9869   0.0173
  -7.500  -0.8096   0.02574   0.01765   0.0024   0.9858   0.0189
  -7.250  -0.7877   0.02489   0.01662   0.0032   0.9835   0.0211
  -7.000  -0.7630   0.02404   0.01556   0.0035   0.9815   0.0228
  -6.750  -0.7401   0.02276   0.01425   0.0039   0.9797   0.0251
  -6.500  -0.7144   0.02221   0.01364   0.0038   0.9780   0.0284
  -6.250  -0.6875   0.02161   0.01289   0.0036   0.9766   0.0317
  -6.000  -0.6658   0.02073   0.01196   0.0043   0.9745   0.0350
  -5.750  -0.6452   0.02024   0.01143   0.0053   0.9713   0.0388
  -5.500  -0.6214   0.01977   0.01085   0.0058   0.9689   0.0421
  -5.250  -0.5973   0.01915   0.01020   0.0060   0.9669   0.0464
  -5.000  -0.5703   0.01868   0.00969   0.0057   0.9653   0.0510
  -4.500  -0.5291   0.01787   0.00879   0.0081   0.9590   0.0624
  -4.250  -0.5051   0.01747   0.00838   0.0085   0.9564   0.0732
  -4.000  -0.4796   0.01700   0.00801   0.0086   0.9542   0.0986
  -3.750  -0.4548   0.01640   0.00764   0.0086   0.9525   0.1548
  -3.500  -0.4393   0.01573   0.00733   0.0106   0.9490   0.2376
  -3.250  -0.4306   0.01479   0.00698   0.0140   0.9441   0.3692
  -3.000  -0.4252   0.01345   0.00661   0.0182   0.9405   0.5691
  -2.750  -0.3953   0.01305   0.00710   0.0185   0.9401   0.7685
  -2.500  -0.3515   0.01352   0.00767   0.0156   0.9401   0.8282
  -2.250  -0.3171   0.01407   0.00820   0.0149   0.9391   0.8661
  -2.000  -0.2716   0.01537   0.00947   0.0126   0.9394   0.8953
  -1.750  -0.2222   0.01593   0.00995   0.0082   0.9397   0.8997
  -1.250  -0.1613   0.01604   0.00992   0.0065   0.9356   0.9097
  -1.000  -0.1289   0.01616   0.01000   0.0052   0.9325   0.9117
  -0.750  -0.0952   0.01622   0.01002   0.0036   0.9301   0.9140
  -0.500  -0.0625   0.01623   0.01001   0.0022   0.9278   0.9170
  -0.250  -0.0396   0.01610   0.00986   0.0030   0.9249   0.9230
   0.000   0.0000   0.01611   0.00986   0.0000   0.9239   0.9239
   0.250   0.0396   0.01610   0.00986  -0.0029   0.9230   0.9249
   0.500   0.0625   0.01623   0.01001  -0.0022   0.9170   0.9278
   0.750   0.0952   0.01622   0.01002  -0.0036   0.9140   0.9301
   1.000   0.1288   0.01616   0.01000  -0.0052   0.9117   0.9326
   1.250   0.1612   0.01604   0.00992  -0.0065   0.9097   0.9356
   1.500   0.1857   0.01603   0.00997  -0.0061   0.9038   0.9386
   1.750   0.2222   0.01593   0.00995  -0.0082   0.8997   0.9398
   2.000   0.2717   0.01536   0.00946  -0.0126   0.8953   0.9394
   2.250   0.3175   0.01406   0.00820  -0.0150   0.8664   0.9390
   2.500   0.3518   0.01351   0.00765  -0.0157   0.8277   0.9401
   2.750   0.3953   0.01305   0.00710  -0.0185   0.7686   0.9401
   3.000   0.4253   0.01345   0.00660  -0.0183   0.5703   0.9405
   3.250   0.4306   0.01478   0.00698  -0.0140   0.3694   0.9442
   3.500   0.4392   0.01572   0.00733  -0.0105   0.2383   0.9491
   3.750   0.4548   0.01640   0.00764  -0.0086   0.1546   0.9525
   4.000   0.4797   0.01700   0.00800  -0.0086   0.0988   0.9542
   4.250   0.5051   0.01747   0.00838  -0.0085   0.0731   0.9564
   4.500   0.5290   0.01787   0.00879  -0.0081   0.0624   0.9591
   5.000   0.5704   0.01868   0.00968  -0.0058   0.0510   0.9653
   5.250   0.5973   0.01915   0.01020  -0.0060   0.0464   0.9670
   5.500   0.6214   0.01976   0.01084  -0.0058   0.0421   0.9690
   5.750   0.6452   0.02024   0.01142  -0.0053   0.0388   0.9713
   6.000   0.6657   0.02073   0.01195  -0.0043   0.0350   0.9746
   6.250   0.6876   0.02161   0.01289  -0.0036   0.0317   0.9766
   6.500   0.7145   0.02220   0.01363  -0.0038   0.0284   0.9780
   6.750   0.7402   0.02277   0.01425  -0.0039   0.0251   0.9797
   7.000   0.7631   0.02403   0.01555  -0.0036   0.0228   0.9815
   7.250   0.7878   0.02488   0.01661  -0.0032   0.0211   0.9836
   7.500   0.8098   0.02575   0.01766  -0.0024   0.0189   0.9858
   7.750   0.8355   0.02667   0.01876  -0.0025   0.0173   0.9870
   8.000   0.8601   0.02772   0.01995  -0.0026   0.0162   0.9884
   8.250   0.8818   0.02956   0.02199  -0.0021   0.0152   0.9899
   8.500   0.9021   0.03163   0.02443  -0.0012   0.0144   0.9916
   8.750   0.9203   0.03351   0.02670   0.0000   0.0134   0.9936
   9.000   0.9361   0.03571   0.02928   0.0015   0.0125   0.9954
   9.250   0.9484   0.03866   0.03266   0.0033   0.0120   0.9975
   9.500   0.9562   0.04198   0.03643   0.0054   0.0116   0.9999
   9.750   0.9467   0.04444   0.03918   0.0112   0.0114   1.0000
  10.000   0.9325   0.04691   0.04191   0.0175   0.0113   1.0000
  10.250   0.9123   0.04927   0.04450   0.0247   0.0112   1.0000
  10.500   0.8859   0.05126   0.04666   0.0327   0.0112   1.0000
  10.750   0.8582   0.05365   0.04923   0.0401   0.0112   1.0000
  11.000   0.8292   0.05659   0.05236   0.0465   0.0112   1.0000
  11.250   0.7980   0.06024   0.05619   0.0518   0.0113   1.0000
  11.500   0.7632   0.06498   0.06110   0.0555   0.0114   1.0000
  11.750   0.7227   0.07172   0.06801   0.0566   0.0116   1.0000
  12.000   0.6766   0.08284   0.07927   0.0522   0.0121   1.0000
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