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LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-080 (lwk80080-il)
Reynolds number: 50,000
Max Cl/Cd: 24.68 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80080-il-50000-n5.txt
Download as CSV file: xf-lwk80080-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-080                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6381   0.09516   0.08818  -0.0122   1.0000   0.0412
  -9.500  -0.6437   0.08912   0.08220  -0.0163   1.0000   0.0407
  -9.250  -0.6524   0.08348   0.07658  -0.0200   1.0000   0.0401
  -9.000  -0.6633   0.07863   0.07173  -0.0224   1.0000   0.0395
  -8.750  -0.6762   0.07428   0.06736  -0.0230   1.0000   0.0390
  -8.500  -0.6865   0.06993   0.06291  -0.0233   1.0000   0.0387
  -8.250  -0.6935   0.06566   0.05847  -0.0231   1.0000   0.0383
  -8.000  -0.6977   0.06139   0.05399  -0.0224   1.0000   0.0380
  -7.750  -0.6985   0.05719   0.04949  -0.0213   1.0000   0.0377
  -7.500  -0.6957   0.05320   0.04517  -0.0200   1.0000   0.0378
  -7.250  -0.6899   0.04935   0.04092  -0.0185   1.0000   0.0380
  -7.000  -0.6813   0.04569   0.03680  -0.0167   1.0000   0.0393
  -6.750  -0.6696   0.04251   0.03310  -0.0149   1.0000   0.0419
  -6.500  -0.6549   0.03958   0.02950  -0.0130   1.0000   0.0442
  -6.250  -0.6380   0.03650   0.02611  -0.0117   1.0000   0.0463
  -6.000  -0.6180   0.03389   0.02321  -0.0104   1.0000   0.0484
  -5.750  -0.5953   0.03152   0.02043  -0.0092   1.0000   0.0516
  -5.500  -0.5716   0.02957   0.01811  -0.0081   1.0000   0.0587
  -5.250  -0.5479   0.02785   0.01630  -0.0072   1.0000   0.0667
  -5.000  -0.5219   0.02604   0.01435  -0.0062   1.0000   0.0741
  -4.750  -0.5005   0.02474   0.01301  -0.0050   1.0000   0.0910
  -4.500  -0.4807   0.02340   0.01160  -0.0033   1.0000   0.1079
  -4.250  -0.4638   0.02208   0.01040  -0.0016   1.0000   0.1368
  -4.000  -0.4499   0.02050   0.00920   0.0004   1.0000   0.1959
  -3.750  -0.4466   0.01839   0.00833   0.0040   1.0000   0.3766
  -3.500  -0.4361   0.01767   0.00912   0.0104   1.0000   0.7043
  -3.250  -0.4210   0.01798   0.00930   0.0150   1.0000   0.7930
  -3.000  -0.3843   0.01862   0.00969   0.0167   1.0000   0.8661
  -2.750  -0.2706   0.01959   0.00979   0.0041   1.0000   0.9303
  -2.500  -0.2149   0.01938   0.00922  -0.0014   1.0000   0.9483
  -2.250  -0.1717   0.01905   0.00864  -0.0050   1.0000   0.9613
  -2.000  -0.1325   0.01872   0.00808  -0.0080   1.0000   0.9726
  -1.750  -0.0956   0.01840   0.00762  -0.0107   1.0000   0.9826
  -1.500  -0.0588   0.01807   0.00718  -0.0134   1.0000   0.9918
  -1.250  -0.0245   0.01782   0.00685  -0.0158   1.0000   1.0000
  -1.000  -0.0147   0.01770   0.00674  -0.0134   1.0000   1.0000
  -0.750  -0.0072   0.01763   0.00665  -0.0107   1.0000   1.0000
  -0.500  -0.0027   0.01760   0.00665  -0.0075   1.0000   1.0000
  -0.250  -0.0006   0.01759   0.00664  -0.0039   1.0000   1.0000
   0.000   0.0000   0.01758   0.00663   0.0000   1.0000   1.0000
   0.250   0.0007   0.01759   0.00664   0.0039   1.0000   1.0000
   0.500   0.0027   0.01759   0.00664   0.0075   1.0000   1.0000
   0.750   0.0072   0.01763   0.00666   0.0107   1.0000   1.0000
   1.000   0.0147   0.01770   0.00672   0.0134   1.0000   1.0000
   1.250   0.0246   0.01782   0.00685   0.0158   1.0000   1.0000
   1.500   0.0583   0.01807   0.00718   0.0135   0.9920   1.0000
   1.750   0.0957   0.01840   0.00762   0.0107   0.9826   1.0000
   2.000   0.1327   0.01872   0.00808   0.0079   0.9725   1.0000
   2.250   0.1717   0.01905   0.00865   0.0050   0.9614   1.0000
   2.500   0.2154   0.01937   0.00921   0.0013   0.9481   1.0000
   2.750   0.2699   0.01959   0.00980  -0.0040   0.9305   1.0000
   3.000   0.3849   0.01860   0.00967  -0.0167   0.8649   1.0000
   3.250   0.4208   0.01799   0.00933  -0.0150   0.7944   1.0000
   3.500   0.4363   0.01768   0.00913  -0.0105   0.7068   1.0000
   3.750   0.4471   0.01834   0.00835  -0.0041   0.3827   1.0000
   4.000   0.4501   0.02047   0.00919  -0.0004   0.1975   1.0000
   4.250   0.4638   0.02208   0.01040   0.0015   0.1352   1.0000
   4.500   0.4806   0.02340   0.01163   0.0033   0.1072   1.0000
   4.750   0.5005   0.02478   0.01305   0.0050   0.0896   1.0000
   5.000   0.5219   0.02607   0.01438   0.0062   0.0737   1.0000
   5.250   0.5482   0.02791   0.01639   0.0072   0.0660   1.0000
   5.500   0.5709   0.02967   0.01817   0.0081   0.0567   1.0000
   5.750   0.5953   0.03157   0.02050   0.0093   0.0511   1.0000
   6.000   0.6176   0.03398   0.02320   0.0104   0.0476   1.0000
   6.250   0.6376   0.03662   0.02618   0.0116   0.0457   1.0000
   6.500   0.6546   0.03960   0.02960   0.0132   0.0435   1.0000
   6.750   0.6690   0.04259   0.03324   0.0151   0.0406   1.0000
   7.000   0.6808   0.04573   0.03686   0.0168   0.0384   1.0000
   7.250   0.6897   0.04935   0.04091   0.0185   0.0377   1.0000
   7.500   0.6955   0.05324   0.04521   0.0200   0.0376   1.0000
   7.750   0.6986   0.05718   0.04948   0.0213   0.0377   1.0000
   8.000   0.6985   0.06123   0.05381   0.0223   0.0380   1.0000
   8.250   0.6943   0.06553   0.05834   0.0230   0.0384   1.0000
   8.500   0.6861   0.07003   0.06301   0.0232   0.0386   1.0000
   8.750   0.6769   0.07423   0.06731   0.0230   0.0391   1.0000
   9.000   0.6639   0.07857   0.07166   0.0223   0.0394   1.0000
   9.250   0.6526   0.08351   0.07661   0.0199   0.0400   1.0000
   9.500   0.6445   0.08904   0.08212   0.0163   0.0407   1.0000
   9.750   0.6392   0.09499   0.08801   0.0122   0.0412   1.0000
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