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NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il)
Reynolds number: 100,000
Max Cl/Cd: 45.13 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf416-il-100000.txt
Download as CSV file: xf-nlf416-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4638   0.08754   0.08257  -0.0553   1.0000   0.0730
 -10.500  -0.5675   0.07190   0.06672  -0.0654   1.0000   0.0645
 -10.250  -0.5730   0.06821   0.06301  -0.0648   1.0000   0.0622
 -10.000  -0.5920   0.06461   0.05939  -0.0638   1.0000   0.0613
  -9.750  -0.6179   0.06169   0.05643  -0.0615   1.0000   0.0604
  -9.500  -0.6430   0.05854   0.05318  -0.0592   1.0000   0.0593
  -9.250  -0.6676   0.05464   0.04903  -0.0568   1.0000   0.0578
  -9.000  -0.7065   0.05050   0.04395  -0.0532   1.0000   0.0543
  -8.750  -0.7014   0.04728   0.04057  -0.0516   1.0000   0.0538
  -8.500  -0.6984   0.04454   0.03753  -0.0498   1.0000   0.0539
  -8.250  -0.6931   0.04205   0.03469  -0.0482   1.0000   0.0543
  -8.000  -0.6831   0.03915   0.03163  -0.0469   1.0000   0.0550
  -7.750  -0.6710   0.03705   0.02944  -0.0456   1.0000   0.0560
  -7.500  -0.6578   0.03515   0.02737  -0.0441   1.0000   0.0566
  -7.250  -0.6437   0.03343   0.02548  -0.0427   1.0000   0.0572
  -7.000  -0.6292   0.03199   0.02391  -0.0412   1.0000   0.0581
  -6.750  -0.6094   0.03066   0.02244  -0.0406   0.9987   0.0596
  -6.500  -0.5611   0.02902   0.02053  -0.0444   0.9901   0.0631
  -6.250  -0.5154   0.02742   0.01911  -0.0481   0.9812   0.0703
  -6.000  -0.4699   0.02585   0.01765  -0.0516   0.9716   0.0804
  -5.750  -0.4274   0.02411   0.01611  -0.0549   0.9599   0.1026
  -5.500  -0.3879   0.02127   0.01422  -0.0593   0.9475   0.2077
  -5.250  -0.3451   0.01921   0.01318  -0.0643   0.9346   0.3755
  -5.000  -0.3062   0.01878   0.01341  -0.0657   0.9211   0.4929
  -4.750  -0.2689   0.01989   0.01472  -0.0644   0.9076   0.5575
  -4.500  -0.2201   0.02127   0.01592  -0.0651   0.8994   0.5936
  -4.250  -0.1788   0.02233   0.01679  -0.0653   0.8854   0.6185
  -4.000  -0.1395   0.02338   0.01766  -0.0646   0.8717   0.6356
  -3.750  -0.0991   0.02417   0.01828  -0.0644   0.8582   0.6517
  -3.500  -0.0583   0.02472   0.01863  -0.0646   0.8449   0.6673
  -3.250  -0.0182   0.02508   0.01879  -0.0651   0.8315   0.6827
  -3.000   0.0155   0.02535   0.01887  -0.0650   0.8160   0.6980
  -2.750   0.0460   0.02574   0.01912  -0.0630   0.8007   0.7066
  -2.500   0.0732   0.02583   0.01906  -0.0619   0.7859   0.7199
  -2.250   0.0988   0.02585   0.01892  -0.0610   0.7727   0.7337
  -2.000   0.1255   0.02582   0.01872  -0.0604   0.7612   0.7477
  -1.750   0.1524   0.02581   0.01859  -0.0591   0.7496   0.7581
  -1.500   0.1752   0.02573   0.01842  -0.0577   0.7385   0.7695
  -1.250   0.2019   0.02559   0.01811  -0.0574   0.7299   0.7819
  -1.000   0.2168   0.02555   0.01803  -0.0555   0.7193   0.7947
  -0.750   0.2491   0.02534   0.01767  -0.0553   0.7114   0.8031
  -0.500   0.2649   0.02522   0.01753  -0.0535   0.7020   0.8137
   0.000   0.3100   0.02494   0.01712  -0.0517   0.6863   0.8320
   0.250   0.3301   0.02487   0.01694  -0.0509   0.6796   0.8417
   0.500   0.3533   0.02471   0.01679  -0.0499   0.6717   0.8486
   0.750   0.3697   0.02469   0.01671  -0.0486   0.6649   0.8570
   1.000   0.3983   0.02451   0.01648  -0.0486   0.6584   0.8631
   1.250   0.4112   0.02456   0.01654  -0.0466   0.6510   0.8704
   1.500   0.4404   0.02439   0.01628  -0.0470   0.6450   0.8758
   1.750   0.4559   0.02446   0.01641  -0.0453   0.6378   0.8816
   2.000   0.4727   0.02452   0.01645  -0.0441   0.6312   0.8871
   2.250   0.5031   0.02442   0.01627  -0.0446   0.6255   0.8913
   2.500   0.5158   0.02459   0.01653  -0.0426   0.6179   0.8962
   2.750   0.5398   0.02461   0.01649  -0.0424   0.6118   0.9004
   3.000   0.5588   0.02475   0.01668  -0.0414   0.6051   0.9041
   3.250   0.5799   0.02484   0.01681  -0.0407   0.5978   0.9079
   3.500   0.6121   0.02483   0.01669  -0.0417   0.5924   0.9114
   3.750   0.6206   0.02525   0.01726  -0.0394   0.5842   0.9151
   4.000   0.6495   0.02522   0.01719  -0.0398   0.5777   0.9180
   4.250   0.6692   0.02551   0.01756  -0.0390   0.5704   0.9211
   4.500   0.6930   0.02565   0.01773  -0.0388   0.5627   0.9241
   4.750   0.7232   0.02575   0.01778  -0.0394   0.5565   0.9270
   5.000   0.7384   0.02618   0.01835  -0.0382   0.5476   0.9298
   5.250   0.7746   0.02606   0.01816  -0.0396   0.5415   0.9321
   5.500   0.7869   0.02661   0.01888  -0.0379   0.5320   0.9352
   5.750   0.8227   0.02649   0.01871  -0.0393   0.5252   0.9374
   6.000   0.8376   0.02707   0.01945  -0.0380   0.5159   0.9406
   6.250   0.8730   0.02693   0.01926  -0.0393   0.5086   0.9431
   6.500   0.8902   0.02748   0.01996  -0.0384   0.4989   0.9457
   6.750   0.9279   0.02725   0.01969  -0.0399   0.4913   0.9477
   7.000   0.9444   0.02780   0.02040  -0.0389   0.4810   0.9512
   7.250   0.9855   0.02741   0.01993  -0.0408   0.4735   0.9540
   7.500   0.9998   0.02802   0.02075  -0.0396   0.4624   0.9578
   7.750   1.0346   0.02791   0.02063  -0.0408   0.4536   0.9604
   8.000   1.0612   0.02804   0.02087  -0.0411   0.4431   0.9640
   8.250   1.0855   0.02832   0.02127  -0.0411   0.4323   0.9685
   8.500   1.1289   0.02782   0.02066  -0.0434   0.4233   0.9725
   8.750   1.1498   0.02822   0.02129  -0.0432   0.4106   0.9811
   9.000   1.1756   0.02843   0.02160  -0.0436   0.3989   1.0000
   9.250   1.2078   0.02826   0.02141  -0.0445   0.3880   1.0000
   9.500   1.2370   0.02821   0.02137  -0.0450   0.3761   1.0000
   9.750   1.2569   0.02859   0.02189  -0.0446   0.3631   1.0000
  10.000   1.2798   0.02890   0.02227  -0.0445   0.3502   1.0000
  10.250   1.3040   0.02919   0.02258  -0.0446   0.3373   1.0000
  10.500   1.3285   0.02953   0.02292  -0.0447   0.3241   1.0000
  10.750   1.3524   0.02997   0.02332  -0.0448   0.3106   1.0000
  11.000   1.3758   0.03055   0.02382  -0.0449   0.2969   1.0000
  11.250   1.3872   0.03150   0.02489  -0.0435   0.2839   1.0000
  11.500   1.3983   0.03257   0.02606  -0.0422   0.2713   1.0000
  11.750   1.4111   0.03369   0.02721  -0.0413   0.2592   1.0000
  12.000   1.4259   0.03481   0.02830  -0.0406   0.2472   1.0000
  12.250   1.4436   0.03591   0.02928  -0.0403   0.2350   1.0000
  12.500   1.4416   0.03766   0.03125  -0.0382   0.2251   1.0000
  12.750   1.4490   0.03930   0.03294  -0.0373   0.2150   1.0000
  13.000   1.4641   0.04067   0.03419  -0.0370   0.2043   1.0000
  13.250   1.4579   0.04299   0.03674  -0.0355   0.1960   1.0000
  13.500   1.4654   0.04489   0.03864  -0.0350   0.1870   1.0000
  13.750   1.4679   0.04700   0.04079  -0.0344   0.1784   1.0000
  14.000   1.4663   0.04966   0.04357  -0.0339   0.1710   1.0000
  14.250   1.4760   0.05149   0.04531  -0.0338   0.1624   1.0000
  14.500   1.4654   0.05501   0.04909  -0.0335   0.1564   1.0000
  14.750   1.4733   0.05703   0.05102  -0.0336   0.1486   1.0000
  15.000   1.4627   0.06091   0.05513  -0.0338   0.1432   1.0000
  15.250   1.4597   0.06403   0.05832  -0.0343   0.1369   1.0000
  15.500   1.4597   0.06717   0.06149  -0.0347   0.1309   1.0000
  15.750   1.4450   0.07181   0.06638  -0.0358   0.1263   1.0000
  16.000   1.4583   0.07350   0.06789  -0.0359   0.1190   1.0000
  16.250   1.4349   0.07949   0.07422  -0.0378   0.1160   1.0000
  16.500   1.4251   0.08400   0.07886  -0.0394   0.1114   1.0000
  16.750   1.4320   0.08653   0.08131  -0.0399   0.1055   1.0000
  17.000   1.4063   0.09362   0.08872  -0.0429   0.1032   1.0000
  17.250   1.3879   0.09993   0.09524  -0.0458   0.1001   1.0000
  17.500   1.4050   0.10087   0.09601  -0.0457   0.0937   1.0000
  17.750   1.3744   0.10948   0.10493  -0.0501   0.0923   1.0000
  18.000   1.3385   0.11956   0.11533  -0.0558   0.0916   1.0000
  18.250   1.2833   0.13423   0.13032  -0.0647   0.0927   1.0000
  18.500   1.3454   0.12592   0.12166  -0.0589   0.0827   1.0000
  18.750   1.3028   0.13822   0.13424  -0.0666   0.0829   1.0000
  19.000   0.9931   0.23535   0.23126  -0.1276   0.1376   1.0000
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