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Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il)
Reynolds number: 50,000
Max Cl/Cd: 32.57 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-apex16-il-50000-n5.txt
Download as CSV file: xf-apex16-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4101   0.11564   0.10869  -0.0429   1.0000   0.1206
  -9.750  -0.4312   0.11340   0.10660  -0.0442   1.0000   0.1251
  -9.500  -0.4642   0.11121   0.10460  -0.0462   1.0000   0.1262
  -9.250  -0.4320   0.10699   0.10032  -0.0417   1.0000   0.1310
  -9.000  -0.4382   0.10434   0.09775  -0.0407   1.0000   0.1351
  -8.750  -0.4710   0.10202   0.09561  -0.0415   1.0000   0.1398
  -8.250  -0.4766   0.09618   0.08991  -0.0375   1.0000   0.1479
  -8.000  -0.5006   0.09366   0.08752  -0.0365   1.0000   0.1511
  -6.000  -0.5683   0.06555   0.05832  -0.0353   0.9962   0.0973
  -5.750  -0.5415   0.06065   0.05299  -0.0368   0.9919   0.0721
  -5.500  -0.5170   0.05729   0.04895  -0.0386   0.9866   0.0671
  -5.250  -0.4935   0.05412   0.04550  -0.0395   0.9819   0.0638
  -5.000  -0.4677   0.05101   0.04205  -0.0408   0.9775   0.0610
  -4.750  -0.4424   0.04836   0.03890  -0.0413   0.9726   0.0582
  -4.250  -0.3847   0.04439   0.03378  -0.0422   0.9631   0.0541
  -4.000  -0.3565   0.04230   0.03141  -0.0428   0.9587   0.0536
  -3.750  -0.3260   0.04049   0.02929  -0.0436   0.9548   0.0534
  -3.500  -0.2990   0.03907   0.02756  -0.0436   0.9496   0.0538
  -3.250  -0.2683   0.03755   0.02586  -0.0445   0.9457   0.0561
  -3.000  -0.2405   0.03637   0.02462  -0.0448   0.9410   0.0587
  -2.750  -0.2117   0.03532   0.02347  -0.0447   0.9361   0.0596
  -2.500  -0.1793   0.03442   0.02249  -0.0451   0.9324   0.0603
  -2.250  -0.1548   0.03369   0.02166  -0.0442   0.9269   0.0615
  -2.000  -0.1280   0.03305   0.02090  -0.0439   0.9216   0.0631
  -1.750  -0.0968   0.03246   0.02012  -0.0447   0.9176   0.0652
  -1.500  -0.0763   0.03189   0.01948  -0.0440   0.9104   0.0689
  -1.250  -0.0457   0.03144   0.01886  -0.0452   0.9054   0.0773
  -1.000  -0.0208   0.03100   0.01827  -0.0453   0.8991   0.0847
  -0.750   0.0080   0.03056   0.01767  -0.0461   0.8931   0.0953
  -0.500   0.0437   0.02962   0.01688  -0.0483   0.8892   0.1564
  -0.250   0.0487   0.02822   0.01761  -0.0438   0.8815   0.6469
   0.000   0.0551   0.02825   0.01828  -0.0367   0.8756   0.7929
   0.250   0.0649   0.02826   0.01843  -0.0317   0.8677   0.8669
   0.500   0.1033   0.02833   0.01832  -0.0342   0.8624   0.8920
   0.750   0.1482   0.02849   0.01832  -0.0382   0.8570   0.9206
   1.000   0.1982   0.02869   0.01838  -0.0436   0.8505   0.9584
   1.250   0.2439   0.02883   0.01834  -0.0481   0.8458   1.0000
   1.750   0.2937   0.02924   0.01843  -0.0490   0.8297   1.0000
   2.000   0.3158   0.02953   0.01862  -0.0488   0.8204   1.0000
   2.250   0.3427   0.02981   0.01879  -0.0493   0.8125   1.0000
   2.500   0.3720   0.03004   0.01896  -0.0501   0.8049   1.0000
   2.750   0.3948   0.03039   0.01925  -0.0499   0.7956   1.0000
   3.000   0.4292   0.03052   0.01936  -0.0513   0.7891   1.0000
   3.250   0.4494   0.03092   0.01974  -0.0505   0.7785   1.0000
   3.500   0.4877   0.03090   0.01974  -0.0524   0.7731   1.0000
   3.750   0.5061   0.03133   0.02019  -0.0513   0.7615   1.0000
   4.000   0.5289   0.03167   0.02058  -0.0508   0.7511   1.0000
   4.250   0.5654   0.03156   0.02054  -0.0521   0.7445   1.0000
   4.500   0.5850   0.03196   0.02100  -0.0511   0.7326   1.0000
   4.750   0.6084   0.03223   0.02138  -0.0505   0.7216   1.0000
   5.000   0.6466   0.03187   0.02115  -0.0517   0.7149   1.0000
   5.500   0.6901   0.03233   0.02183  -0.0498   0.6897   1.0000
   5.750   0.7156   0.03233   0.02202  -0.0492   0.6774   1.0000
   6.000   0.7441   0.03213   0.02198  -0.0487   0.6651   1.0000
   6.250   0.7737   0.03176   0.02179  -0.0483   0.6517   1.0000
   6.500   0.8016   0.03135   0.02156  -0.0474   0.6358   1.0000
   6.750   0.8309   0.03075   0.02120  -0.0465   0.6180   1.0000
   7.000   0.8652   0.02988   0.02052  -0.0460   0.5990   1.0000
   7.250   0.8854   0.02981   0.02062  -0.0442   0.5760   1.0000
   7.500   0.9135   0.02939   0.02036  -0.0431   0.5519   1.0000
   7.750   0.9348   0.02936   0.02053  -0.0413   0.5242   1.0000
   8.000   0.9524   0.02953   0.02082  -0.0392   0.4922   1.0000
   8.250   0.9693   0.02976   0.02108  -0.0369   0.4549   1.0000
   8.500   0.9792   0.03024   0.02135  -0.0336   0.4031   1.0000
   8.750   0.9788   0.03139   0.02209  -0.0296   0.3400   1.0000
   9.000   0.9755   0.03303   0.02330  -0.0260   0.2796   1.0000
   9.250   0.9737   0.03490   0.02483  -0.0231   0.2305   1.0000
   9.500   0.9733   0.03690   0.02660  -0.0206   0.1894   1.0000
   9.750   0.9725   0.03913   0.02867  -0.0183   0.1521   1.0000
  10.000   0.9716   0.04155   0.03088  -0.0163   0.1221   1.0000
  10.250   0.9719   0.04402   0.03320  -0.0145   0.1005   1.0000
  10.500   0.9749   0.04637   0.03551  -0.0128   0.0878   1.0000
  10.750   0.9802   0.04859   0.03774  -0.0113   0.0794   1.0000
  11.000   0.9903   0.05058   0.03986  -0.0100   0.0724   1.0000
  11.250   0.9982   0.05267   0.04195  -0.0089   0.0666   1.0000
  11.500   1.0123   0.05452   0.04402  -0.0078   0.0606   1.0000
  11.750   1.0273   0.05638   0.04598  -0.0069   0.0566   1.0000
  12.000   1.0520   0.05821   0.04798  -0.0060   0.0535   1.0000
  12.250   1.0735   0.06061   0.05080  -0.0052   0.0508   1.0000
  12.500   1.0818   0.06336   0.05383  -0.0044   0.0480   1.0000
  12.750   1.0865   0.06613   0.05677  -0.0036   0.0458   1.0000
  13.000   1.0949   0.06912   0.05975  -0.0031   0.0436   1.0000
  13.250   1.0910   0.07298   0.06403  -0.0024   0.0430   1.0000
  13.500   1.0831   0.07725   0.06866  -0.0019   0.0426   1.0000
  13.750   1.0710   0.08191   0.07365  -0.0020   0.0423   1.0000
  14.000   1.0555   0.08704   0.07909  -0.0027   0.0421   1.0000
  14.250   1.0381   0.09262   0.08492  -0.0040   0.0421   1.0000
  14.500   1.0179   0.09888   0.09142  -0.0063   0.0422   1.0000
  14.750   0.9964   0.10585   0.09860  -0.0095   0.0423   1.0000
  15.000   0.9748   0.11349   0.10640  -0.0136   0.0426   1.0000
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