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NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il)
Reynolds number: 100,000
Max Cl/Cd: 33.09 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls417mod-il-100000.txt
Download as CSV file: xf-ls417mod-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4297   0.11906   0.11380  -0.0391   1.0000   0.1603
 -11.000  -0.3927   0.11569   0.11041  -0.0353   1.0000   0.1621
 -10.750  -0.6595   0.07259   0.06685  -0.0619   1.0000   0.0854
 -10.500  -0.6273   0.06972   0.06414  -0.0619   1.0000   0.0865
 -10.000  -0.7529   0.06160   0.05537  -0.0509   1.0000   0.0778
  -9.750  -0.7602   0.05899   0.05268  -0.0480   1.0000   0.0774
  -9.500  -0.7669   0.05630   0.04986  -0.0452   1.0000   0.0770
  -9.250  -0.7717   0.05346   0.04682  -0.0427   1.0000   0.0765
  -9.000  -0.7735   0.05045   0.04355  -0.0405   1.0000   0.0757
  -8.750  -0.7718   0.04726   0.04003  -0.0386   1.0000   0.0748
  -8.500  -0.7655   0.04421   0.03657  -0.0371   1.0000   0.0743
  -8.250  -0.7540   0.04160   0.03361  -0.0359   1.0000   0.0742
  -8.000  -0.7390   0.03938   0.03109  -0.0349   1.0000   0.0747
  -7.750  -0.7221   0.03752   0.02889  -0.0341   1.0000   0.0763
  -7.500  -0.7031   0.03578   0.02669  -0.0335   1.0000   0.0781
  -7.250  -0.6825   0.03441   0.02543  -0.0328   1.0000   0.0799
  -7.000  -0.6612   0.03315   0.02408  -0.0320   1.0000   0.0817
  -6.750  -0.6392   0.03193   0.02267  -0.0313   1.0000   0.0837
  -6.500  -0.6172   0.03080   0.02145  -0.0305   1.0000   0.0864
  -6.250  -0.5958   0.02998   0.02071  -0.0298   1.0000   0.0902
  -6.000  -0.5735   0.02911   0.01975  -0.0291   1.0000   0.0942
  -5.750  -0.5518   0.02830   0.01908  -0.0284   1.0000   0.0984
  -5.500  -0.5295   0.02753   0.01835  -0.0277   1.0000   0.1039
  -5.250  -0.5066   0.02690   0.01778  -0.0273   1.0000   0.1122
  -5.000  -0.4648   0.02593   0.01712  -0.0305   0.9951   0.1276
  -4.750  -0.4149   0.02451   0.01619  -0.0356   0.9883   0.1728
  -4.500  -0.3584   0.02161   0.01551  -0.0436   0.9828   0.4661
  -4.250  -0.3261   0.02269   0.01709  -0.0423   0.9735   0.5895
  -4.000  -0.2861   0.02416   0.01848  -0.0425   0.9654   0.6375
  -3.750  -0.2620   0.02543   0.01972  -0.0396   0.9546   0.6635
  -3.500  -0.2359   0.02681   0.02106  -0.0365   0.9448   0.6846
  -3.250  -0.2043   0.02801   0.02219  -0.0342   0.9352   0.7034
  -3.000  -0.1792   0.02873   0.02284  -0.0317   0.9237   0.7209
  -2.750  -0.1337   0.02926   0.02326  -0.0326   0.9157   0.7395
  -2.500  -0.1150   0.02969   0.02366  -0.0282   0.9026   0.7508
  -2.250  -0.0638   0.02986   0.02374  -0.0294   0.8959   0.7680
  -2.000  -0.0387   0.02978   0.02360  -0.0272   0.8816   0.7844
  -1.750   0.0220   0.02924   0.02294  -0.0313   0.8753   0.8005
  -1.500   0.0510   0.02871   0.02237  -0.0293   0.8600   0.8093
  -1.250   0.0926   0.02786   0.02143  -0.0309   0.8473   0.8205
  -1.000   0.1387   0.02689   0.02038  -0.0321   0.8334   0.8289
  -0.750   0.1673   0.02606   0.01948  -0.0312   0.8132   0.8391
  -0.500   0.2031   0.02513   0.01846  -0.0309   0.7899   0.8473
  -0.250   0.2297   0.02430   0.01750  -0.0297   0.7607   0.8562
   0.000   0.2586   0.02353   0.01658  -0.0285   0.7199   0.8638
   0.250   0.2774   0.02302   0.01585  -0.0265   0.6723   0.8719
   0.500   0.3062   0.02259   0.01509  -0.0258   0.6252   0.8782
   0.750   0.3269   0.02247   0.01460  -0.0246   0.5924   0.8853
   1.000   0.3533   0.02234   0.01421  -0.0243   0.5653   0.8904
   1.250   0.3792   0.02234   0.01396  -0.0241   0.5449   0.8959
   1.500   0.4001   0.02246   0.01382  -0.0234   0.5294   0.9011
   1.750   0.4279   0.02243   0.01369  -0.0236   0.5142   0.9053
   2.000   0.4554   0.02254   0.01364  -0.0239   0.5018   0.9096
   2.250   0.4782   0.02267   0.01365  -0.0236   0.4905   0.9141
   2.500   0.5038   0.02285   0.01372  -0.0237   0.4806   0.9175
   2.750   0.5312   0.02295   0.01378  -0.0240   0.4704   0.9210
   3.000   0.5598   0.02328   0.01392  -0.0246   0.4617   0.9246
   3.250   0.5812   0.02343   0.01415  -0.0242   0.4532   0.9278
   3.500   0.6066   0.02366   0.01433  -0.0243   0.4451   0.9309
   3.750   0.6363   0.02404   0.01460  -0.0251   0.4376   0.9341
   4.000   0.6598   0.02424   0.01491  -0.0249   0.4298   0.9373
   4.250   0.6855   0.02455   0.01518  -0.0251   0.4226   0.9401
   4.500   0.7133   0.02516   0.01564  -0.0258   0.4162   0.9432
   4.750   0.7367   0.02536   0.01604  -0.0256   0.4092   0.9467
   5.000   0.7624   0.02570   0.01642  -0.0258   0.4022   0.9502
   5.250   0.7909   0.02617   0.01680  -0.0265   0.3961   0.9531
   5.500   0.8144   0.02678   0.01748  -0.0265   0.3901   0.9563
   5.750   0.8396   0.02719   0.01804  -0.0267   0.3832   0.9597
   6.000   0.8677   0.02762   0.01847  -0.0274   0.3769   0.9638
   6.250   0.8988   0.02842   0.01913  -0.0286   0.3713   0.9677
   6.500   0.9211   0.02895   0.01995  -0.0286   0.3649   0.9717
   6.750   0.9485   0.02952   0.02061  -0.0294   0.3583   0.9756
   7.000   0.9798   0.03004   0.02108  -0.0306   0.3526   0.9797
   7.250   1.0087   0.03100   0.02215  -0.0319   0.3468   0.9838
   7.500   1.0348   0.03180   0.02315  -0.0327   0.3398   0.9894
   7.750   1.0688   0.03237   0.02374  -0.0346   0.3337   0.9953
   8.000   1.0984   0.03319   0.02443  -0.0357   0.3288   1.0000
   8.250   1.1079   0.03429   0.02590  -0.0340   0.3227   1.0000
   8.500   1.1316   0.03509   0.02680  -0.0344   0.3167   1.0000
   8.750   1.1644   0.03557   0.02718  -0.0358   0.3115   1.0000
   9.000   1.1835   0.03697   0.02878  -0.0359   0.3059   1.0000
   9.250   1.2019   0.03818   0.03022  -0.0358   0.2994   1.0000
   9.500   1.2347   0.03860   0.03058  -0.0373   0.2939   1.0000
   9.750   1.2617   0.03968   0.03169  -0.0383   0.2888   1.0000
  10.000   1.2699   0.04149   0.03386  -0.0372   0.2823   1.0000
  10.250   1.3013   0.04189   0.03424  -0.0385   0.2767   1.0000
  10.500   1.3364   0.04248   0.03472  -0.0403   0.2718   1.0000
  10.750   1.3305   0.04504   0.03774  -0.0378   0.2657   1.0000
  11.000   1.3585   0.04553   0.03825  -0.0387   0.2601   1.0000
  11.250   1.4029   0.04547   0.03798  -0.0412   0.2553   1.0000
  11.500   1.3782   0.04899   0.04203  -0.0371   0.2500   1.0000
  11.750   1.3950   0.04998   0.04310  -0.0368   0.2447   1.0000
  12.000   1.4582   0.04871   0.04150  -0.0409   0.2394   1.0000
  12.250   1.4076   0.05334   0.04668  -0.0344   0.2359   1.0000
  12.500   1.3608   0.05876   0.05247  -0.0306   0.2324   1.0000
  12.750   1.4566   0.05420   0.04754  -0.0350   0.2259   1.0000
  13.000   1.4331   0.05804   0.05162  -0.0323   0.2226   1.0000
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