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NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il)
Reynolds number: 100,000
Max Cl/Cd: 28.64 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf415-il-100000-n5.txt
Download as CSV file: xf-nlf415-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF(2)-0415 AIRFOIL                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3708   0.10393   0.09860  -0.1007   0.9529   0.0305
 -11.750  -0.3734   0.09840   0.09307  -0.1038   0.9511   0.0301
 -11.500  -0.3790   0.09260   0.08725  -0.1074   0.9495   0.0297
 -11.250  -0.3868   0.08696   0.08156  -0.1110   0.9480   0.0290
 -11.000  -0.4010   0.08125   0.07577  -0.1146   0.9463   0.0287
 -10.750  -0.4254   0.07817   0.07265  -0.1129   0.9416   0.0285
 -10.500  -0.4447   0.07447   0.06887  -0.1130   0.9384   0.0281
 -10.250  -0.4631   0.07090   0.06516  -0.1132   0.9357   0.0282
 -10.000  -0.4777   0.06742   0.06152  -0.1135   0.9334   0.0281
  -9.750  -0.5065   0.06652   0.06057  -0.1078   0.9283   0.0279
  -9.500  -0.5328   0.06531   0.05928  -0.1025   0.9244   0.0278
  -9.250  -0.5494   0.06308   0.05688  -0.0990   0.9216   0.0273
  -9.000  -0.5581   0.06064   0.05423  -0.0965   0.9196   0.0277
  -8.750  -0.5674   0.05849   0.05187  -0.0930   0.9172   0.0277
  -8.500  -0.5859   0.05738   0.05063  -0.0868   0.9135   0.0278
  -8.250  -0.5941   0.05539   0.04841  -0.0826   0.9113   0.0280
  -8.000  -0.5957   0.05312   0.04587  -0.0794   0.9095   0.0278
  -7.750  -0.5924   0.05060   0.04304  -0.0768   0.9080   0.0274
  -7.500  -0.5827   0.04802   0.04011  -0.0751   0.9066   0.0270
  -7.250  -0.5685   0.04545   0.03717  -0.0738   0.9054   0.0268
  -7.000  -0.5522   0.04322   0.03456  -0.0725   0.9045   0.0267
  -6.750  -0.5335   0.04127   0.03228  -0.0715   0.9039   0.0267
  -6.500  -0.5195   0.03978   0.03054  -0.0694   0.9029   0.0268
  -6.250  -0.5086   0.03857   0.02914  -0.0666   0.9017   0.0270
  -6.000  -0.4954   0.03755   0.02795  -0.0643   0.9001   0.0278
  -5.750  -0.4793   0.03670   0.02690  -0.0624   0.8986   0.0294
  -5.500  -0.4609   0.03576   0.02579  -0.0608   0.8976   0.0301
  -5.250  -0.4422   0.03487   0.02479  -0.0591   0.8967   0.0305
  -5.000  -0.4237   0.03407   0.02390  -0.0575   0.8958   0.0309
  -4.750  -0.4049   0.03331   0.02312  -0.0560   0.8946   0.0313
  -4.500  -0.3869   0.03241   0.02226  -0.0546   0.8933   0.0322
  -4.250  -0.3688   0.03175   0.02159  -0.0534   0.8922   0.0331
  -4.000  -0.3498   0.03124   0.02105  -0.0524   0.8913   0.0344
  -3.750  -0.3285   0.03084   0.02058  -0.0519   0.8904   0.0370
  -3.500  -0.3038   0.03051   0.02012  -0.0519   0.8894   0.0406
  -3.250  -0.2859   0.03003   0.01954  -0.0509   0.8877   0.0442
  -3.000  -0.2711   0.02974   0.01917  -0.0493   0.8860   0.0483
  -2.750  -0.2525   0.02934   0.01874  -0.0484   0.8842   0.0598
  -2.500  -0.2362   0.02734   0.01898  -0.0489   0.8825   0.5701
  -2.250  -0.2209   0.02898   0.02067  -0.0449   0.8804   0.6266
  -2.000  -0.2067   0.03037   0.02211  -0.0404   0.8786   0.6561
  -1.750  -0.1881   0.03127   0.02300  -0.0374   0.8768   0.6743
  -1.500  -0.1637   0.03168   0.02331  -0.0365   0.8754   0.6845
  -1.250  -0.1345   0.03169   0.02314  -0.0377   0.8745   0.6852
  -1.000  -0.1158   0.03167   0.02301  -0.0369   0.8720   0.6860
  -0.750  -0.0966   0.03166   0.02290  -0.0362   0.8691   0.6869
  -0.500  -0.0734   0.03171   0.02287  -0.0362   0.8670   0.6882
  -0.250  -0.0472   0.03177   0.02282  -0.0368   0.8649   0.6893
   0.000  -0.0190   0.03184   0.02281  -0.0377   0.8630   0.6901
   0.250   0.0102   0.03196   0.02285  -0.0388   0.8615   0.6910
   0.500   0.0412   0.03210   0.02292  -0.0402   0.8601   0.6919
   0.750   0.0612   0.03222   0.02300  -0.0397   0.8568   0.6929
   1.000   0.0812   0.03235   0.02309  -0.0393   0.8533   0.6940
   1.250   0.1073   0.03251   0.02322  -0.0398   0.8505   0.6953
   1.500   0.1351   0.03270   0.02341  -0.0405   0.8482   0.6964
   1.750   0.1651   0.03291   0.02363  -0.0415   0.8463   0.6973
   2.000   0.1971   0.03315   0.02390  -0.0429   0.8447   0.6982
   2.250   0.2071   0.03334   0.02413  -0.0405   0.8385   0.6993
   2.500   0.2330   0.03356   0.02439  -0.0409   0.8351   0.7003
   2.750   0.2628   0.03378   0.02466  -0.0419   0.8326   0.7013
   3.000   0.2955   0.03402   0.02498  -0.0434   0.8306   0.7025
   3.250   0.3092   0.03427   0.02529  -0.0417   0.8240   0.7037
   3.500   0.3362   0.03450   0.02560  -0.0422   0.8200   0.7050
   3.750   0.3681   0.03471   0.02590  -0.0436   0.8173   0.7064
   4.250   0.4154   0.03513   0.02652  -0.0434   0.8059   0.7098
   4.500   0.4524   0.03463   0.02615  -0.0448   0.7966   0.7113
   4.750   0.4961   0.03301   0.02471  -0.0460   0.7788   0.7127
   5.000   0.5394   0.03116   0.02302  -0.0471   0.7609   0.7142
   5.250   0.5606   0.03027   0.02227  -0.0454   0.7419   0.7158
   5.500   0.5761   0.02991   0.02206  -0.0432   0.7225   0.7175
   5.750   0.5900   0.02970   0.02203  -0.0409   0.6993   0.7193
   6.000   0.6033   0.02960   0.02208  -0.0385   0.6684   0.7212
   6.250   0.6956   0.02429   0.01525  -0.0425   0.3632   0.7232
   6.500   0.7054   0.02562   0.01578  -0.0402   0.2325   0.7251
   6.750   0.7245   0.02642   0.01626  -0.0393   0.1746   0.7268
   7.000   0.7440   0.02715   0.01683  -0.0385   0.1429   0.7286
   7.250   0.7638   0.02785   0.01750  -0.0376   0.1238   0.7307
   7.500   0.7832   0.02860   0.01825  -0.0368   0.1092   0.7332
   7.750   0.8022   0.02941   0.01903  -0.0360   0.0980   0.7360
   8.000   0.8226   0.03018   0.01989  -0.0353   0.0894   0.7389
   8.250   0.8423   0.03107   0.02082  -0.0345   0.0826   0.7415
   8.500   0.8628   0.03187   0.02173  -0.0338   0.0756   0.7441
   8.750   0.8847   0.03284   0.02276  -0.0333   0.0701   0.7470
   9.000   0.9076   0.03371   0.02377  -0.0330   0.0639   0.7501
   9.250   0.9306   0.03480   0.02488  -0.0328   0.0587   0.7535
   9.500   0.9528   0.03572   0.02602  -0.0324   0.0526   0.7568
   9.750   0.9718   0.03684   0.02719  -0.0318   0.0475   0.7602
  10.000   0.9921   0.03785   0.02849  -0.0311   0.0419   0.7642
  10.250   1.0079   0.03909   0.02970  -0.0303   0.0379   0.7687
  10.500   1.0307   0.04059   0.03160  -0.0298   0.0335   0.7730
  10.750   1.0439   0.04179   0.03291  -0.0286   0.0306   0.7782
  11.000   1.0618   0.04366   0.03503  -0.0278   0.0281   0.7842
  11.250   1.0779   0.04575   0.03756  -0.0267   0.0258   0.7899
  11.500   1.0894   0.04780   0.03989  -0.0252   0.0244   0.7971
  11.750   1.0972   0.04975   0.04207  -0.0235   0.0235   0.8048
  12.000   1.1031   0.05200   0.04452  -0.0217   0.0228   0.8141
  12.250   1.1028   0.05517   0.04812  -0.0193   0.0222   0.8242
  12.500   1.0957   0.05874   0.05220  -0.0163   0.0218   0.8366
  12.750   1.0827   0.06249   0.05642  -0.0132   0.0214   0.8541
  13.000   1.0661   0.06608   0.06047  -0.0100   0.0213   0.8914
  13.250   1.0455   0.07018   0.06492  -0.0077   0.0211   1.0000
  13.500   1.0238   0.07531   0.07035  -0.0065   0.0210   1.0000
  13.750   1.0001   0.08094   0.07625  -0.0063   0.0210   1.0000
  14.000   0.9753   0.08714   0.08268  -0.0073   0.0211   1.0000
  14.250   0.9481   0.09448   0.09023  -0.0099   0.0213   1.0000
  14.500   0.9210   0.10308   0.09899  -0.0143   0.0216   1.0000
  14.750   0.8933   0.11371   0.10974  -0.0211   0.0219   1.0000
  15.000   0.8667   0.12677   0.12285  -0.0296   0.0223   1.0000
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