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Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il)
Reynolds number: 200,000
Max Cl/Cd: 81.41 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-apex16-il-200000.txt
Download as CSV file: xf-apex16-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Apex 16 (normalized using XFOIL date021206)     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4588   0.09649   0.09326  -0.0391   1.0000   0.0378
  -8.750  -0.4763   0.09304   0.08987  -0.0398   1.0000   0.0380
  -8.500  -0.4960   0.08978   0.08665  -0.0399   1.0000   0.0380
  -8.250  -0.5048   0.08468   0.08148  -0.0470   0.9952   0.0381
  -8.000  -0.5111   0.08065   0.07717  -0.0540   0.9864   0.0388
  -7.750  -0.5081   0.07768   0.07389  -0.0574   0.9786   0.0392
  -7.500  -0.4963   0.07449   0.07041  -0.0599   0.9733   0.0393
  -7.250  -0.4868   0.06518   0.06119  -0.0632   0.9713   0.0405
  -7.000  -0.4795   0.06166   0.05766  -0.0628   0.9649   0.0414
  -6.750  -0.4614   0.05810   0.05402  -0.0647   0.9607   0.0428
  -6.500  -0.4375   0.05476   0.05048  -0.0675   0.9578   0.0454
  -6.250  -0.4212   0.05654   0.05164  -0.0652   0.9486   0.0508
  -6.000  -0.4050   0.05024   0.04510  -0.0671   0.9453   0.0522
  -5.750  -0.3796   0.04596   0.04085  -0.0696   0.9435   0.0541
  -5.500  -0.3710   0.04391   0.03871  -0.0676   0.9360   0.0559
  -5.250  -0.3446   0.04182   0.03640  -0.0685   0.9324   0.0602
  -5.000  -0.3132   0.03976   0.03381  -0.0698   0.9298   0.0667
  -4.750  -0.3006   0.03737   0.03143  -0.0684   0.9234   0.0690
  -4.500  -0.2698   0.03886   0.03245  -0.0681   0.9187   0.0789
  -4.250  -0.2442   0.03354   0.02713  -0.0701   0.9167   0.0836
  -4.000  -0.2102   0.03196   0.02526  -0.0719   0.9149   0.0971
  -3.750  -0.2002   0.03120   0.02433  -0.0692   0.9066   0.1112
  -3.500  -0.1715   0.02880   0.02188  -0.0705   0.9038   0.1280
  -2.750  -0.0637   0.02461   0.01667  -0.0687   0.8939   0.0515
  -2.500  -0.0320   0.02293   0.01499  -0.0692   0.8908   0.0498
  -2.250   0.0045   0.02219   0.01417  -0.0707   0.8884   0.0512
  -2.000   0.0416   0.02093   0.01290  -0.0724   0.8869   0.0513
  -1.750   0.0558   0.02026   0.01224  -0.0699   0.8792   0.0517
  -1.500   0.0854   0.01925   0.01125  -0.0703   0.8756   0.0536
  -1.250   0.1215   0.01847   0.01046  -0.0721   0.8735   0.0577
  -1.000   0.1608   0.01787   0.00975  -0.0744   0.8720   0.0659
  -0.750   0.1736   0.01776   0.00958  -0.0716   0.8626   0.0749
  -0.500   0.1967   0.01564   0.00917  -0.0711   0.8599   0.5764
  -0.250   0.2324   0.01526   0.00906  -0.0721   0.8582   0.6666
   0.000   0.2453   0.01539   0.00933  -0.0688   0.8495   0.7111
   0.250   0.2776   0.01517   0.00926  -0.0689   0.8465   0.7565
   0.500   0.3186   0.01485   0.00893  -0.0712   0.8446   0.7747
   0.750   0.3604   0.01448   0.00857  -0.0738   0.8430   0.7907
   1.000   0.3753   0.01455   0.00868  -0.0711   0.8335   0.8070
   1.250   0.4140   0.01419   0.00835  -0.0729   0.8307   0.8236
   1.500   0.4552   0.01379   0.00797  -0.0752   0.8285   0.8405
   1.750   0.4710   0.01379   0.00803  -0.0726   0.8190   0.8598
   2.000   0.5096   0.01339   0.00767  -0.0744   0.8156   0.8785
   2.250   0.5390   0.01321   0.00756  -0.0745   0.8090   0.8987
   2.500   0.5777   0.01296   0.00737  -0.0765   0.8031   0.9192
   2.750   0.6302   0.01263   0.00708  -0.0813   0.7995   0.9366
   3.000   0.6741   0.01261   0.00713  -0.0848   0.7906   0.9567
   3.250   0.7281   0.01234   0.00690  -0.0901   0.7850   0.9702
   3.500   0.7744   0.01228   0.00690  -0.0942   0.7748   0.9871
   3.750   0.8144   0.01212   0.00676  -0.0969   0.7642   1.0000
   4.000   0.8324   0.01194   0.00653  -0.0949   0.7503   1.0000
   4.250   0.8520   0.01181   0.00639  -0.0931   0.7352   1.0000
   4.500   0.8744   0.01178   0.00635  -0.0920   0.7216   1.0000
   4.750   0.8973   0.01178   0.00636  -0.0909   0.7082   1.0000
   5.000   0.9188   0.01182   0.00641  -0.0895   0.6934   1.0000
   5.250   0.9388   0.01188   0.00650  -0.0879   0.6764   1.0000
   5.500   0.9589   0.01192   0.00652  -0.0861   0.6550   1.0000
   5.750   0.9763   0.01201   0.00655  -0.0838   0.6278   1.0000
   6.000   0.9924   0.01219   0.00662  -0.0812   0.5965   1.0000
   6.250   1.0062   0.01247   0.00680  -0.0783   0.5614   1.0000
   6.500   1.0163   0.01284   0.00702  -0.0747   0.5198   1.0000
   6.750   1.0229   0.01332   0.00729  -0.0706   0.4719   1.0000
   7.000   1.0257   0.01391   0.00764  -0.0658   0.4244   1.0000
   7.250   1.0270   0.01463   0.00812  -0.0609   0.3756   1.0000
   7.500   1.0281   0.01549   0.00872  -0.0562   0.3250   1.0000
   7.750   1.0301   0.01645   0.00943  -0.0520   0.2724   1.0000
   8.000   1.0310   0.01760   0.01026  -0.0478   0.2156   1.0000
   8.500   1.0243   0.02092   0.01265  -0.0390   0.0850   1.0000
   8.750   1.0258   0.02248   0.01399  -0.0354   0.0618   1.0000
   9.000   1.0341   0.02363   0.01518  -0.0329   0.0544   1.0000
   9.250   1.0380   0.02509   0.01664  -0.0298   0.0499   1.0000
   9.500   1.0480   0.02622   0.01789  -0.0277   0.0463   1.0000
   9.750   1.0565   0.02749   0.01919  -0.0255   0.0431   1.0000
  10.000   1.0611   0.02929   0.02098  -0.0230   0.0409   1.0000
  10.250   1.0733   0.03066   0.02245  -0.0213   0.0390   1.0000
  10.500   1.0869   0.03189   0.02378  -0.0198   0.0367   1.0000
  10.750   1.1009   0.03327   0.02523  -0.0184   0.0346   1.0000
  11.000   1.1192   0.03490   0.02685  -0.0176   0.0329   1.0000
  11.250   1.1518   0.03746   0.02952  -0.0182   0.0309   1.0000
  11.500   1.1656   0.03894   0.03123  -0.0167   0.0296   1.0000
  11.750   1.1814   0.04082   0.03332  -0.0156   0.0284   1.0000
  12.000   1.1975   0.04313   0.03588  -0.0146   0.0276   1.0000
  12.250   1.2096   0.04574   0.03877  -0.0132   0.0272   1.0000
  12.500   1.2157   0.04861   0.04193  -0.0114   0.0269   1.0000
  12.750   1.2154   0.05175   0.04538  -0.0092   0.0268   1.0000
  13.000   1.2116   0.05477   0.04865  -0.0070   0.0265   1.0000
  13.250   1.2014   0.05827   0.05245  -0.0046   0.0266   1.0000
  13.500   1.1830   0.06263   0.05718  -0.0023   0.0271   1.0000
  13.750   1.1805   0.06511   0.05974  -0.0013   0.0261   1.0000
  14.000   1.1569   0.06990   0.06486   0.0000   0.0265   1.0000
  14.250   1.1451   0.07367   0.06879   0.0004   0.0260   1.0000
  14.500   1.0987   0.08233   0.07792  -0.0002   0.0281   1.0000
  14.750   1.0735   0.08860   0.08441  -0.0019   0.0285   1.0000
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