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NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NLF(1)-0115 (nlf0115-il)
Reynolds number: 50,000
Max Cl/Cd: 30.74 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf0115-il-50000.txt
Download as CSV file: xf-nlf0115-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLF(1)-0115                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3575   0.12529   0.11804  -0.0305   1.0000   0.2934
 -10.750  -0.3585   0.12271   0.11554  -0.0299   1.0000   0.3061
  -9.750  -0.3481   0.11241   0.10549  -0.0253   1.0000   0.3678
  -9.500  -0.3387   0.10947   0.10260  -0.0239   1.0000   0.3848
  -9.250  -0.3294   0.10673   0.09991  -0.0225   1.0000   0.4024
  -9.000  -0.3215   0.10419   0.09742  -0.0208   1.0000   0.4219
  -8.500  -0.3218   0.10012   0.09352  -0.0166   1.0000   0.4617
  -7.750  -0.4609   0.08469   0.07874  -0.0232   1.0000   0.3083
  -7.500  -0.5196   0.08110   0.07540  -0.0214   1.0000   0.2924
  -7.250  -0.5677   0.07910   0.07358  -0.0170   1.0000   0.2923
  -7.000  -0.6188   0.07631   0.07089  -0.0135   1.0000   0.2901
  -6.750  -0.6736   0.07316   0.06770  -0.0107   1.0000   0.2872
  -6.500  -0.7022   0.06426   0.05796  -0.0146   1.0000   0.2009
  -6.250  -0.7090   0.05939   0.05198  -0.0134   1.0000   0.1585
  -6.000  -0.6994   0.05565   0.04774  -0.0117   1.0000   0.1424
  -5.750  -0.6879   0.05207   0.04385  -0.0102   1.0000   0.1337
  -5.500  -0.6742   0.04955   0.04075  -0.0084   1.0000   0.1255
  -5.250  -0.6591   0.04683   0.03769  -0.0069   1.0000   0.1211
  -5.000  -0.6421   0.04451   0.03478  -0.0052   1.0000   0.1163
  -4.750  -0.6241   0.04276   0.03253  -0.0036   1.0000   0.1150
  -4.500  -0.6051   0.04086   0.03046  -0.0025   1.0000   0.1163
  -4.250  -0.5851   0.03926   0.02866  -0.0013   1.0000   0.1176
  -4.000  -0.5640   0.03780   0.02700  -0.0001   1.0000   0.1186
  -3.750  -0.5419   0.03651   0.02554   0.0011   1.0000   0.1199
  -3.500  -0.0995   0.04027   0.03188  -0.0317   1.0000   1.0000
  -3.250  -0.0982   0.04027   0.03173  -0.0293   1.0000   1.0000
  -3.000  -0.0961   0.04026   0.03159  -0.0270   1.0000   1.0000
  -2.750  -0.0934   0.04026   0.03145  -0.0248   1.0000   1.0000
  -2.500  -0.0901   0.04026   0.03132  -0.0226   1.0000   1.0000
  -2.250  -0.0863   0.04026   0.03119  -0.0205   1.0000   1.0000
  -2.000  -0.0822   0.04027   0.03108  -0.0183   1.0000   1.0000
  -1.750  -0.0778   0.04029   0.03099  -0.0163   1.0000   1.0000
  -1.500  -0.0732   0.04030   0.03091  -0.0142   1.0000   1.0000
  -1.250  -0.0684   0.04033   0.03082  -0.0121   1.0000   1.0000
  -1.000  -0.0635   0.04036   0.03077  -0.0101   1.0000   1.0000
  -0.750  -0.0585   0.04039   0.03072  -0.0080   1.0000   1.0000
  -0.500  -0.0536   0.04043   0.03068  -0.0059   1.0000   1.0000
  -0.250  -0.0487   0.04047   0.03065  -0.0039   1.0000   1.0000
   0.000  -0.0438   0.04051   0.03063  -0.0018   1.0000   1.0000
   0.250  -0.0392   0.04055   0.03061   0.0003   1.0000   1.0000
   0.500  -0.0348   0.04059   0.03059   0.0024   1.0000   1.0000
   0.750  -0.0306   0.04062   0.03058   0.0045   1.0000   1.0000
   1.000  -0.0268   0.04065   0.03057   0.0067   1.0000   1.0000
   1.250  -0.0233   0.04067   0.03056   0.0089   1.0000   1.0000
   1.500  -0.0204   0.04067   0.03053   0.0112   1.0000   1.0000
   1.750  -0.0180   0.04065   0.03049   0.0135   1.0000   1.0000
   2.000  -0.0162   0.04060   0.03043   0.0158   1.0000   1.0000
   2.250  -0.0152   0.04053   0.03034   0.0182   1.0000   1.0000
   2.500  -0.0149   0.04042   0.03023   0.0207   1.0000   1.0000
   2.750  -0.0151   0.04028   0.03009   0.0232   1.0000   1.0000
   3.000  -0.0151   0.04014   0.02995   0.0256   1.0000   1.0000
   3.250  -0.0141   0.04008   0.02989   0.0277   1.0000   1.0000
   3.500  -0.0097   0.04024   0.03003   0.0291   1.0000   1.0000
   3.750  -0.0013   0.04070   0.03048   0.0296   1.0000   1.0000
   4.000   0.0100   0.04140   0.03119   0.0296   1.0000   1.0000
   4.250   0.2704   0.04854   0.03845  -0.0079   0.8393   1.0000
   4.500   0.2829   0.04868   0.03862  -0.0064   0.8160   1.0000
   4.750   0.3308   0.04920   0.03921  -0.0094   0.7905   1.0000
   5.000   0.3546   0.04941   0.03947  -0.0092   0.7655   1.0000
   5.250   0.3961   0.04954   0.03969  -0.0108   0.7405   1.0000
   5.500   0.4377   0.04935   0.03960  -0.0120   0.7152   1.0000
   5.750   0.4709   0.04913   0.03948  -0.0121   0.6892   1.0000
   6.000   0.5324   0.04769   0.03823  -0.0142   0.6657   1.0000
   6.250   0.5629   0.04691   0.03757  -0.0131   0.6381   1.0000
   6.500   0.6437   0.04304   0.03399  -0.0150   0.6174   1.0000
   6.750   0.6823   0.04072   0.03181  -0.0133   0.5891   1.0000
   7.000   0.7464   0.03665   0.02796  -0.0132   0.5590   1.0000
   7.250   0.8145   0.03249   0.02388  -0.0138   0.5171   1.0000
   7.500   0.8810   0.02967   0.02073  -0.0155   0.4636   1.0000
   7.750   0.9128   0.02989   0.02055  -0.0151   0.4212   1.0000
   8.000   0.9482   0.03085   0.02114  -0.0160   0.3864   1.0000
   8.250   0.9713   0.03222   0.02241  -0.0156   0.3612   1.0000
   8.500   1.0037   0.03370   0.02368  -0.0166   0.3384   1.0000
   8.750   1.0273   0.03531   0.02532  -0.0164   0.3209   1.0000
   9.000   1.0514   0.03701   0.02702  -0.0164   0.3053   1.0000
   9.250   1.0759   0.03879   0.02880  -0.0164   0.2911   1.0000
   9.500   1.1002   0.04069   0.03073  -0.0164   0.2790   1.0000
   9.750   1.1065   0.04276   0.03312  -0.0140   0.2700   1.0000
  10.000   1.1269   0.04484   0.03525  -0.0136   0.2597   1.0000
  10.250   1.1333   0.04711   0.03778  -0.0114   0.2521   1.0000
  10.500   1.1480   0.04959   0.04037  -0.0105   0.2446   1.0000
  10.750   1.1380   0.05226   0.04338  -0.0066   0.2395   1.0000
  11.000   1.1648   0.05464   0.04572  -0.0071   0.2306   1.0000
  11.250   1.1414   0.05784   0.04930  -0.0023   0.2284   1.0000
  11.500   1.1133   0.06130   0.05304   0.0024   0.2270   1.0000
  11.750   1.0777   0.06537   0.05732   0.0069   0.2266   1.0000
  12.000   1.0295   0.07097   0.06309   0.0100   0.2276   1.0000
  12.250   0.9720   0.07892   0.07113   0.0106   0.2297   1.0000
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