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NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il)
Reynolds number: 50,000
Max Cl/Cd: 25.73 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf416-il-50000-n5.txt
Download as CSV file: xf-nlf416-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF(1)-0416 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4517   0.10417   0.09665  -0.0488   1.0000   0.0457
 -11.750  -0.4649   0.09707   0.08957  -0.0522   1.0000   0.0453
 -11.500  -0.4845   0.08935   0.08186  -0.0563   1.0000   0.0449
 -11.250  -0.5069   0.08219   0.07467  -0.0601   1.0000   0.0444
 -11.000  -0.5321   0.07582   0.06822  -0.0632   1.0000   0.0439
 -10.750  -0.5570   0.07050   0.06280  -0.0650   1.0000   0.0436
 -10.500  -0.5798   0.06617   0.05836  -0.0655   1.0000   0.0435
 -10.250  -0.6004   0.06257   0.05464  -0.0649   1.0000   0.0433
 -10.000  -0.6205   0.05959   0.05152  -0.0632   1.0000   0.0435
  -9.750  -0.6385   0.05697   0.04877  -0.0609   1.0000   0.0437
  -9.500  -0.6494   0.05421   0.04581  -0.0591   1.0000   0.0441
  -9.250  -0.6567   0.05148   0.04282  -0.0571   1.0000   0.0449
  -9.000  -0.6597   0.04892   0.03991  -0.0551   1.0000   0.0458
  -8.750  -0.6534   0.04692   0.03786  -0.0534   1.0000   0.0469
  -8.500  -0.6455   0.04517   0.03605  -0.0517   1.0000   0.0483
  -8.250  -0.6364   0.04335   0.03409  -0.0499   1.0000   0.0499
  -8.000  -0.6250   0.04157   0.03213  -0.0480   1.0000   0.0513
  -7.750  -0.6118   0.03994   0.03028  -0.0460   1.0000   0.0531
  -7.500  -0.5992   0.03858   0.02888  -0.0440   1.0000   0.0555
  -7.250  -0.5887   0.03750   0.02783  -0.0420   1.0000   0.0588
  -7.000  -0.5764   0.03649   0.02665  -0.0398   1.0000   0.0629
  -6.750  -0.5666   0.03553   0.02578  -0.0375   1.0000   0.0667
  -6.500  -0.5358   0.03435   0.02452  -0.0387   0.9931   0.0756
  -6.250  -0.4990   0.03286   0.02312  -0.0416   0.9814   0.0904
  -6.000  -0.4665   0.03118   0.02162  -0.0442   0.9675   0.1162
  -5.750  -0.4371   0.02926   0.02010  -0.0468   0.9521   0.1637
  -5.500  -0.4079   0.02736   0.01875  -0.0497   0.9364   0.2431
  -5.250  -0.3781   0.02590   0.01789  -0.0519   0.9212   0.3419
  -5.000  -0.3483   0.02553   0.01803  -0.0518   0.9064   0.4305
  -4.750  -0.3168   0.02624   0.01895  -0.0499   0.8922   0.4933
  -4.500  -0.2807   0.02722   0.01982  -0.0488   0.8795   0.5371
  -4.000  -0.2065   0.02865   0.02072  -0.0491   0.8523   0.5980
  -3.750  -0.1721   0.02912   0.02092  -0.0492   0.8381   0.6206
  -3.500  -0.1380   0.02945   0.02101  -0.0492   0.8245   0.6404
  -3.250  -0.1034   0.02962   0.02091  -0.0496   0.8118   0.6587
  -3.000  -0.0699   0.02972   0.02076  -0.0497   0.7992   0.6744
  -2.750  -0.0417   0.02976   0.02060  -0.0492   0.7852   0.6885
  -2.250   0.0155   0.02963   0.02004  -0.0489   0.7607   0.7158
  -2.000   0.0434   0.02959   0.01981  -0.0482   0.7491   0.7266
  -1.750   0.0679   0.02953   0.01960  -0.0474   0.7373   0.7369
  -1.500   0.0956   0.02938   0.01925  -0.0475   0.7275   0.7483
  -1.250   0.1200   0.02932   0.01907  -0.0465   0.7168   0.7572
  -1.000   0.1445   0.02921   0.01882  -0.0461   0.7072   0.7665
  -0.750   0.1701   0.02911   0.01858  -0.0458   0.6982   0.7756
  -0.500   0.1929   0.02905   0.01842  -0.0450   0.6890   0.7834
  -0.250   0.2184   0.02896   0.01821  -0.0448   0.6810   0.7917
   0.000   0.2409   0.02893   0.01810  -0.0441   0.6726   0.7988
   0.250   0.2655   0.02887   0.01796  -0.0438   0.6647   0.8058
   0.500   0.2892   0.02886   0.01786  -0.0435   0.6572   0.8125
   0.750   0.3114   0.02887   0.01784  -0.0427   0.6494   0.8184
   1.000   0.3400   0.02883   0.01767  -0.0433   0.6432   0.8246
   1.250   0.3571   0.02896   0.01783  -0.0419   0.6347   0.8299
   1.500   0.3843   0.02894   0.01774  -0.0420   0.6285   0.8351
   1.750   0.4038   0.02915   0.01794  -0.0414   0.6209   0.8407
   2.000   0.4269   0.02922   0.01800  -0.0409   0.6140   0.8450
   2.250   0.4547   0.02925   0.01797  -0.0411   0.6082   0.8494
   2.500   0.4710   0.02959   0.01836  -0.0400   0.6000   0.8544
   2.750   0.4991   0.02965   0.01839  -0.0404   0.5941   0.8583
   3.000   0.5175   0.02995   0.01873  -0.0394   0.5868   0.8625
   3.250   0.5407   0.03017   0.01897  -0.0391   0.5797   0.8664
   3.500   0.5707   0.03028   0.01905  -0.0398   0.5742   0.8701
   3.750   0.5849   0.03081   0.01969  -0.0385   0.5656   0.8739
   4.000   0.6141   0.03089   0.01975  -0.0389   0.5597   0.8771
   4.250   0.6307   0.03142   0.02038  -0.0380   0.5518   0.8809
   4.500   0.6563   0.03170   0.02071  -0.0381   0.5448   0.8843
   4.750   0.6822   0.03203   0.02107  -0.0384   0.5381   0.8874
   5.000   0.6992   0.03256   0.02171  -0.0374   0.5296   0.8906
   5.250   0.7338   0.03250   0.02165  -0.0384   0.5241   0.8935
   5.500   0.7426   0.03347   0.02279  -0.0368   0.5143   0.8975
   5.750   0.7767   0.03347   0.02280  -0.0378   0.5081   0.9003
   6.000   0.7871   0.03444   0.02394  -0.0365   0.4985   0.9036
   6.250   0.8184   0.03446   0.02401  -0.0370   0.4918   0.9067
   6.500   0.8292   0.03544   0.02516  -0.0357   0.4823   0.9110
   6.750   0.8607   0.03548   0.02525  -0.0363   0.4751   0.9145
   7.000   0.8702   0.03656   0.02652  -0.0349   0.4654   0.9188
   7.250   0.9027   0.03649   0.02652  -0.0355   0.4581   0.9222
   7.500   0.9090   0.03778   0.02800  -0.0340   0.4477   0.9271
   7.750   0.9460   0.03746   0.02775  -0.0350   0.4407   0.9310
   8.000   0.9456   0.03904   0.02955  -0.0329   0.4295   0.9381
   8.250   0.9878   0.03839   0.02894  -0.0342   0.4228   0.9434
   8.500   0.9835   0.04026   0.03105  -0.0322   0.4110   0.9552
   8.750   0.9930   0.04137   0.03233  -0.0313   0.4011   0.9925
   9.000   1.0264   0.04125   0.03230  -0.0322   0.3924   1.0000
   9.250   1.0197   0.04380   0.03502  -0.0309   0.3809   1.0000
   9.500   1.0491   0.04385   0.03516  -0.0314   0.3723   1.0000
   9.750   1.0582   0.04538   0.03684  -0.0311   0.3619   1.0000
  10.000   1.0507   0.04850   0.04009  -0.0307   0.3505   1.0000
  10.250   1.0975   0.04686   0.03851  -0.0312   0.3428   1.0000
  10.500   1.0852   0.05053   0.04233  -0.0311   0.3313   1.0000
  10.750   1.0782   0.05412   0.04604  -0.0316   0.3203   1.0000
  11.000   1.1352   0.05100   0.04296  -0.0313   0.3127   1.0000
  11.250   1.1070   0.05692   0.04904  -0.0322   0.3010   1.0000
  11.500   1.1045   0.06040   0.05263  -0.0330   0.2907   1.0000
  11.750   1.1495   0.05810   0.05035  -0.0322   0.2825   1.0000
  12.000   1.1169   0.06543   0.05784  -0.0342   0.2713   1.0000
  12.250   1.1376   0.06603   0.05852  -0.0342   0.2627   1.0000
  12.500   1.1427   0.06869   0.06126  -0.0349   0.2532   1.0000
  12.750   1.1114   0.07676   0.06946  -0.0377   0.2431   1.0000
  13.000   1.1691   0.07186   0.06455  -0.0354   0.2360   1.0000
  13.250   1.1045   0.08522   0.07809  -0.0406   0.2254   1.0000
  13.500   1.1618   0.07992   0.07280  -0.0378   0.2192   1.0000
  13.750   1.0930   0.09484   0.08789  -0.0441   0.2090   1.0000
  14.000   1.0648   0.10390   0.09702  -0.0481   0.1999   1.0000
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