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NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il)
Reynolds number: 50,000
Max Cl/Cd: 23.5 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf414f-il-50000-n5.txt
Download as CSV file: xf-nlf414f-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF 0414F AIRFOIL                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4030   0.09924   0.09206  -0.0814   0.9659   0.0496
 -10.250  -0.4075   0.09555   0.08838  -0.0823   0.9642   0.0492
 -10.000  -0.4158   0.09168   0.08452  -0.0834   0.9624   0.0488
  -9.750  -0.4285   0.08799   0.08082  -0.0840   0.9609   0.0484
  -9.500  -0.4452   0.08469   0.07751  -0.0838   0.9595   0.0480
  -9.250  -0.4647   0.08173   0.07450  -0.0828   0.9578   0.0476
  -9.000  -0.4915   0.07991   0.07268  -0.0790   0.9551   0.0472
  -8.750  -0.5138   0.07760   0.07031  -0.0758   0.9530   0.0468
  -8.500  -0.5319   0.07498   0.06761  -0.0730   0.9512   0.0466
  -8.250  -0.5448   0.07207   0.06451  -0.0708   0.9490   0.0464
  -8.000  -0.5532   0.06904   0.06127  -0.0689   0.9471   0.0463
  -7.750  -0.5584   0.06608   0.05806  -0.0670   0.9457   0.0464
  -7.500  -0.5580   0.06301   0.05468  -0.0656   0.9443   0.0466
  -7.250  -0.5579   0.06026   0.05161  -0.0635   0.9424   0.0468
  -7.000  -0.5555   0.05763   0.04865  -0.0612   0.9407   0.0470
  -6.750  -0.5489   0.05500   0.04565  -0.0593   0.9393   0.0472
  -6.500  -0.5378   0.05241   0.04266  -0.0579   0.9377   0.0472
  -6.250  -0.5224   0.04994   0.03980  -0.0569   0.9360   0.0473
  -6.000  -0.5037   0.04765   0.03708  -0.0562   0.9345   0.0475
  -5.750  -0.4827   0.04559   0.03462  -0.0556   0.9332   0.0480
  -5.500  -0.4595   0.04377   0.03240  -0.0551   0.9321   0.0487
  -5.250  -0.4340   0.04220   0.03049  -0.0549   0.9308   0.0501
  -5.000  -0.4080   0.04096   0.02920  -0.0551   0.9295   0.0530
  -4.750  -0.3854   0.03996   0.02805  -0.0543   0.9280   0.0559
  -4.500  -0.3638   0.03906   0.02695  -0.0528   0.9265   0.0584
  -4.250  -0.3418   0.03824   0.02605  -0.0513   0.9251   0.0609
  -4.000  -0.3210   0.03760   0.02538  -0.0500   0.9233   0.0659
  -3.750  -0.2992   0.03704   0.02467  -0.0488   0.9213   0.0720
  -3.500  -0.2780   0.03634   0.02400  -0.0480   0.9194   0.0799
  -3.250  -0.2555   0.03567   0.02332  -0.0476   0.9176   0.0927
  -3.000  -0.2313   0.03483   0.02263  -0.0477   0.9157   0.1188
  -2.750  -0.2155   0.03189   0.02210  -0.0477   0.9143   0.4486
  -2.250  -0.2235   0.03441   0.02527  -0.0289   0.9077   0.8032
  -2.000  -0.2266   0.03489   0.02574  -0.0187   0.9048   0.8610
  -1.750  -0.1546   0.03586   0.02633  -0.0216   0.9055   0.9391
  -1.500  -0.1186   0.03600   0.02617  -0.0241   0.9031   0.9450
  -1.250  -0.0817   0.03622   0.02611  -0.0268   0.9008   0.9505
  -1.000  -0.0543   0.03638   0.02608  -0.0278   0.8980   0.9566
  -0.750  -0.0242   0.03651   0.02604  -0.0295   0.8944   0.9610
  -0.500   0.0046   0.03671   0.02608  -0.0309   0.8909   0.9658
  -0.250   0.0326   0.03698   0.02620  -0.0321   0.8876   0.9702
   0.000   0.0689   0.03738   0.02647  -0.0348   0.8847   0.9730
   0.250   0.0886   0.03755   0.02657  -0.0346   0.8798   0.9771
   0.500   0.1128   0.03784   0.02678  -0.0351   0.8752   0.9808
   0.750   0.1428   0.03825   0.02712  -0.0366   0.8714   0.9840
   1.000   0.1676   0.03861   0.02742  -0.0373   0.8664   0.9872
   1.250   0.1890   0.03892   0.02771  -0.0373   0.8606   0.9909
   1.750   0.2383   0.03974   0.02850  -0.0384   0.8496   0.9976
   2.000   0.2594   0.04012   0.02888  -0.0382   0.8434   1.0000
   2.250   0.2762   0.04049   0.02925  -0.0371   0.8374   1.0000
   2.500   0.2838   0.04069   0.02948  -0.0344   0.8293   1.0000
   2.750   0.3111   0.04121   0.03002  -0.0350   0.8246   1.0000
   3.250   0.3391   0.04180   0.03068  -0.0317   0.8094   1.0000
   3.750   0.3754   0.04251   0.03150  -0.0299   0.7939   1.0000
   4.000   0.3841   0.04277   0.03183  -0.0278   0.7831   1.0000
   4.250   0.4138   0.04326   0.03240  -0.0288   0.7768   1.0000
   4.500   0.4310   0.04360   0.03284  -0.0280   0.7665   1.0000
   4.750   0.4534   0.04397   0.03332  -0.0280   0.7571   1.0000
   5.000   0.4846   0.04430   0.03377  -0.0291   0.7493   1.0000
   5.250   0.5041   0.04459   0.03419  -0.0286   0.7379   1.0000
   5.500   0.5277   0.04482   0.03459  -0.0287   0.7270   1.0000
   5.750   0.5546   0.04488   0.03481  -0.0289   0.7155   1.0000
   6.000   0.5830   0.04435   0.03444  -0.0288   0.6997   1.0000
   6.250   0.6175   0.04308   0.03338  -0.0286   0.6815   1.0000
   6.500   0.6420   0.04211   0.03258  -0.0273   0.6599   1.0000
   6.750   0.6700   0.04110   0.03178  -0.0265   0.6391   1.0000
   7.000   0.6976   0.03999   0.03089  -0.0254   0.6160   1.0000
   7.250   0.7233   0.03873   0.02986  -0.0238   0.5873   1.0000
   7.500   0.7424   0.03803   0.02934  -0.0218   0.5456   1.0000
   7.750   0.7814   0.03548   0.02670  -0.0199   0.4653   1.0000
   8.000   0.8105   0.03449   0.02458  -0.0171   0.3141   1.0000
   8.250   0.8132   0.03642   0.02584  -0.0149   0.2374   1.0000
   8.500   0.8192   0.03837   0.02737  -0.0134   0.1916   1.0000
   8.750   0.8292   0.04013   0.02887  -0.0123   0.1624   1.0000
   9.000   0.8426   0.04171   0.03034  -0.0114   0.1412   1.0000
   9.250   0.8591   0.04313   0.03169  -0.0107   0.1258   1.0000
   9.500   0.8788   0.04439   0.03294  -0.0102   0.1135   1.0000
   9.750   0.9027   0.04551   0.03405  -0.0099   0.1043   1.0000
  10.000   0.9303   0.04651   0.03512  -0.0099   0.0955   1.0000
  10.250   0.9664   0.04744   0.03617  -0.0103   0.0884   1.0000
  10.500   1.0001   0.04863   0.03748  -0.0108   0.0828   1.0000
  10.750   1.0334   0.05016   0.03908  -0.0115   0.0780   1.0000
  11.000   1.0628   0.05209   0.04133  -0.0118   0.0740   1.0000
  11.250   1.0901   0.05424   0.04371  -0.0121   0.0714   1.0000
  11.500   1.1137   0.05642   0.04599  -0.0124   0.0690   1.0000
  11.750   1.1279   0.05919   0.04905  -0.0119   0.0669   1.0000
  12.000   1.1318   0.06221   0.05252  -0.0106   0.0652   1.0000
  12.250   1.1329   0.06541   0.05610  -0.0093   0.0639   1.0000
  12.500   1.1306   0.06889   0.05992  -0.0080   0.0630   1.0000
  12.750   1.1236   0.07264   0.06400  -0.0067   0.0625   1.0000
  13.000   1.1119   0.07671   0.06841  -0.0056   0.0621   1.0000
  13.250   1.0956   0.08120   0.07320  -0.0047   0.0619   1.0000
  13.500   1.0745   0.08627   0.07856  -0.0043   0.0618   1.0000
  13.750   1.0484   0.09215   0.08471  -0.0049   0.0619   1.0000
  14.000   1.0165   0.09927   0.09209  -0.0067   0.0622   1.0000
  14.250   0.9784   0.10838   0.10143  -0.0108   0.0628   1.0000
  14.500   0.9361   0.12047   0.11369  -0.0180   0.0636   1.0000
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