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NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il)
Reynolds number: 50,000
Max Cl/Cd: 21.1 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf415-il-50000-n5.txt
Download as CSV file: xf-nlf415-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5860   0.11377   0.10724  -0.0477   0.9976   0.0513
 -10.250  -0.5928   0.10927   0.10275  -0.0486   0.9967   0.0503
 -10.000  -0.6053   0.10448   0.09796  -0.0499   0.9957   0.0494
  -9.750  -0.6214   0.09968   0.09313  -0.0513   0.9945   0.0487
  -9.500  -0.6413   0.09517   0.08858  -0.0519   0.9930   0.0480
  -9.250  -0.6636   0.09130   0.08465  -0.0516   0.9914   0.0475
  -9.000  -0.6891   0.08819   0.08147  -0.0499   0.9901   0.0471
  -8.750  -0.7129   0.08527   0.07846  -0.0476   0.9891   0.0467
  -8.500  -0.7299   0.08179   0.07481  -0.0459   0.9878   0.0461
  -8.250  -0.7422   0.07797   0.07075  -0.0445   0.9863   0.0453
  -8.000  -0.7499   0.07413   0.06660  -0.0431   0.9850   0.0444
  -7.750  -0.7551   0.07043   0.06254  -0.0412   0.9843   0.0435
  -7.500  -0.7562   0.06686   0.05853  -0.0392   0.9836   0.0426
  -7.250  -0.7523   0.06347   0.05459  -0.0375   0.9825   0.0418
  -7.000  -0.7430   0.06037   0.05108  -0.0362   0.9814   0.0417
  -6.750  -0.7305   0.05752   0.04802  -0.0354   0.9805   0.0425
  -6.500  -0.7170   0.05504   0.04532  -0.0345   0.9799   0.0436
  -6.250  -0.7015   0.05268   0.04263  -0.0336   0.9794   0.0447
  -6.000  -0.6830   0.05037   0.03996  -0.0327   0.9785   0.0453
  -5.750  -0.6618   0.04820   0.03743  -0.0319   0.9775   0.0454
  -5.500  -0.6390   0.04625   0.03515  -0.0311   0.9766   0.0456
  -5.250  -0.6158   0.04461   0.03324  -0.0301   0.9758   0.0461
  -5.000  -0.5924   0.04323   0.03165  -0.0288   0.9753   0.0468
  -4.750  -0.5679   0.04230   0.03056  -0.0273   0.9747   0.0477
  -4.500  -0.5434   0.04174   0.02984  -0.0256   0.9739   0.0501
  -4.250  -0.5195   0.04138   0.02927  -0.0239   0.9729   0.0525
  -4.000  -0.5036   0.04060   0.02855  -0.0214   0.9718   0.0549
  -3.750  -0.4885   0.03984   0.02774  -0.0193   0.9708   0.0570
  -3.500  -0.4727   0.03902   0.02680  -0.0177   0.9696   0.0595
  -3.250  -0.4551   0.03818   0.02580  -0.0167   0.9680   0.0629
  -3.000  -0.4357   0.03732   0.02480  -0.0164   0.9665   0.0673
  -2.750  -0.4146   0.03641   0.02382  -0.0165   0.9652   0.0784
  -2.500  -0.3908   0.03499   0.02262  -0.0179   0.9639   0.1095
  -2.250  -0.3814   0.03479   0.02469  -0.0141   0.9622   0.6233
  -1.750  -0.3888   0.03899   0.02917   0.0081   0.9579   0.7386
  -1.500  -0.3832   0.03952   0.02961   0.0149   0.9556   0.7640
  -1.250  -0.3587   0.03928   0.02907   0.0141   0.9535   0.7659
  -1.000  -0.3325   0.03910   0.02861   0.0129   0.9514   0.7670
  -0.750  -0.3043   0.03902   0.02829   0.0113   0.9492   0.7677
  -0.500  -0.2746   0.03907   0.02811   0.0094   0.9472   0.7686
  -0.250  -0.2491   0.03896   0.02779   0.0083   0.9446   0.7698
   0.000  -0.2254   0.03887   0.02757   0.0078   0.9418   0.7708
   0.250  -0.1998   0.03888   0.02745   0.0070   0.9390   0.7717
   0.500  -0.1720   0.03900   0.02745   0.0056   0.9363   0.7724
   0.750  -0.1420   0.03926   0.02758   0.0039   0.9337   0.7732
   1.000  -0.1168   0.03935   0.02759   0.0031   0.9303   0.7743
   1.250  -0.0927   0.03943   0.02761   0.0025   0.9267   0.7757
   1.500  -0.0653   0.03966   0.02778   0.0013   0.9232   0.7773
   1.750  -0.0347   0.04004   0.02811  -0.0005   0.9200   0.7787
   2.000  -0.0072   0.04032   0.02837  -0.0018   0.9162   0.7800
   2.250   0.0174   0.04050   0.02854  -0.0025   0.9115   0.7814
   2.500   0.0469   0.04089   0.02892  -0.0042   0.9074   0.7827
   2.750   0.0807   0.04147   0.02951  -0.0067   0.9038   0.7842
   3.000   0.1014   0.04161   0.02970  -0.0066   0.8979   0.7857
   3.250   0.1287   0.04201   0.03017  -0.0076   0.8929   0.7874
   3.500   0.1620   0.04265   0.03089  -0.0097   0.8888   0.7894
   3.750   0.1814   0.04283   0.03115  -0.0094   0.8817   0.7915
   4.000   0.2126   0.04338   0.03181  -0.0111   0.8763   0.7937
   4.250   0.2384   0.04380   0.03234  -0.0120   0.8695   0.7959
   4.500   0.2679   0.04429   0.03296  -0.0136   0.8628   0.7980
   4.750   0.2964   0.04478   0.03360  -0.0148   0.8556   0.8000
   5.000   0.3247   0.04522   0.03424  -0.0159   0.8477   0.8021
   5.250   0.3508   0.04559   0.03480  -0.0165   0.8386   0.8045
   5.500   0.3882   0.04607   0.03551  -0.0189   0.8305   0.8073
   5.750   0.4227   0.04575   0.03545  -0.0201   0.8122   0.8104
   6.000   0.4752   0.04412   0.03410  -0.0225   0.7834   0.8137
   6.250   0.5135   0.04222   0.03249  -0.0225   0.7546   0.8168
   6.500   0.5398   0.04083   0.03142  -0.0212   0.7282   0.8203
   6.750   0.5587   0.03978   0.03065  -0.0192   0.6975   0.8242
   7.000   0.5776   0.03877   0.02991  -0.0171   0.6575   0.8283
   7.250   0.5934   0.03793   0.02937  -0.0144   0.6004   0.8320
   7.500   0.6624   0.03396   0.02355  -0.0133   0.2805   0.8359
   7.750   0.6712   0.03555   0.02464  -0.0114   0.2190   0.8403
   8.000   0.6858   0.03685   0.02568  -0.0103   0.1835   0.8453
   8.250   0.7046   0.03785   0.02666  -0.0093   0.1599   0.8509
   8.500   0.7279   0.03880   0.02756  -0.0091   0.1407   0.8575
   8.750   0.7589   0.03950   0.02834  -0.0093   0.1260   0.8647
   9.250   0.8543   0.04108   0.03024  -0.0139   0.0980   0.8825
   9.500   0.8949   0.04242   0.03185  -0.0157   0.0870   0.8944
   9.750   0.9372   0.04447   0.03435  -0.0178   0.0774   0.9099
  10.000   0.9709   0.04676   0.03694  -0.0194   0.0701   0.9380
  10.250   0.9921   0.04897   0.03957  -0.0194   0.0633   1.0000
  10.500   1.0139   0.05188   0.04268  -0.0200   0.0584   1.0000
  10.750   1.0231   0.05508   0.04644  -0.0185   0.0541   1.0000
  11.000   1.0315   0.05787   0.04950  -0.0173   0.0511   1.0000
  11.250   1.0412   0.06047   0.05214  -0.0166   0.0486   1.0000
  11.500   1.0322   0.06411   0.05623  -0.0135   0.0471   1.0000
  11.750   1.0187   0.06794   0.06050  -0.0105   0.0461   1.0000
  12.000   1.0027   0.07191   0.06482  -0.0078   0.0453   1.0000
  12.250   0.9836   0.07615   0.06937  -0.0055   0.0447   1.0000
  12.500   0.9628   0.08072   0.07421  -0.0040   0.0445   1.0000
  12.750   0.9395   0.08577   0.07950  -0.0032   0.0445   1.0000
  13.000   0.9151   0.09136   0.08528  -0.0034   0.0447   1.0000
  13.250   0.8893   0.09771   0.09179  -0.0049   0.0451   1.0000
  13.500   0.8639   0.10495   0.09915  -0.0079   0.0456   1.0000
  13.750   0.8409   0.11309   0.10735  -0.0124   0.0463   1.0000
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