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LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-100 (lwk80100-il)
Reynolds number: 50,000
Max Cl/Cd: 26.44 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80100-il-50000-n5.txt
Download as CSV file: xf-lwk80100-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-100                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6523   0.09359   0.08647  -0.0225   1.0000   0.0491
 -10.500  -0.6674   0.08632   0.07922  -0.0273   1.0000   0.0485
 -10.250  -0.6863   0.07999   0.07287  -0.0310   1.0000   0.0475
 -10.000  -0.7070   0.07455   0.06737  -0.0330   1.0000   0.0463
  -9.750  -0.7278   0.07007   0.06280  -0.0331   1.0000   0.0460
  -9.500  -0.7456   0.06629   0.05887  -0.0317   1.0000   0.0459
  -9.250  -0.7572   0.06260   0.05498  -0.0302   1.0000   0.0464
  -9.000  -0.7654   0.05890   0.05102  -0.0284   1.0000   0.0473
  -8.750  -0.7700   0.05516   0.04695  -0.0263   1.0000   0.0481
  -8.500  -0.7700   0.05153   0.04294  -0.0243   1.0000   0.0487
  -8.250  -0.7663   0.04798   0.03894  -0.0221   1.0000   0.0495
  -8.000  -0.7589   0.04458   0.03503  -0.0200   1.0000   0.0508
  -7.750  -0.7488   0.04162   0.03154  -0.0179   1.0000   0.0537
  -7.500  -0.7335   0.03959   0.02945  -0.0167   1.0000   0.0575
  -7.250  -0.7162   0.03724   0.02678  -0.0153   1.0000   0.0610
  -7.000  -0.6954   0.03481   0.02384  -0.0139   1.0000   0.0650
  -6.750  -0.6761   0.03305   0.02203  -0.0128   1.0000   0.0715
  -6.500  -0.6522   0.03129   0.01992  -0.0118   1.0000   0.0785
  -6.250  -0.6286   0.02967   0.01834  -0.0111   1.0000   0.0861
  -6.000  -0.6063   0.02838   0.01697  -0.0100   1.0000   0.0975
  -5.750  -0.5836   0.02712   0.01559  -0.0088   1.0000   0.1087
  -5.500  -0.5669   0.02605   0.01456  -0.0071   1.0000   0.1245
  -5.250  -0.5526   0.02500   0.01353  -0.0049   1.0000   0.1419
  -5.000  -0.5412   0.02394   0.01259  -0.0023   1.0000   0.1662
  -4.750  -0.5329   0.02282   0.01174   0.0006   1.0000   0.2038
  -4.500  -0.5280   0.02153   0.01094   0.0039   1.0000   0.2693
  -4.250  -0.5281   0.02001   0.01034   0.0083   1.0000   0.4034
  -4.000  -0.5145   0.01986   0.01143   0.0139   1.0000   0.6372
  -3.750  -0.5054   0.02018   0.01162   0.0186   1.0000   0.7149
  -3.500  -0.4945   0.02054   0.01182   0.0230   1.0000   0.7640
  -3.250  -0.4781   0.02101   0.01213   0.0267   1.0000   0.8049
  -3.000  -0.4510   0.02164   0.01258   0.0290   1.0000   0.8455
  -2.750  -0.4001   0.02245   0.01306   0.0272   1.0000   0.8854
  -2.500  -0.3308   0.02289   0.01313   0.0206   1.0000   0.9090
  -2.250  -0.2830   0.02283   0.01283   0.0166   1.0000   0.9224
  -2.000  -0.2441   0.02269   0.01247   0.0139   1.0000   0.9335
  -1.750  -0.2118   0.02253   0.01216   0.0121   1.0000   0.9442
  -1.500  -0.1782   0.02237   0.01187   0.0100   1.0000   0.9535
  -1.250  -0.1451   0.02221   0.01160   0.0079   1.0000   0.9617
  -1.000  -0.1160   0.02210   0.01140   0.0065   1.0000   0.9706
  -0.750  -0.0843   0.02198   0.01123   0.0045   1.0000   0.9785
  -0.500  -0.0540   0.02189   0.01110   0.0027   1.0000   0.9861
  -0.250  -0.0237   0.02183   0.01101   0.0008   1.0000   0.9940
   0.000   0.0001   0.02186   0.01103   0.0000   1.0000   1.0000
   0.250   0.0238   0.02183   0.01101  -0.0007   0.9940   1.0000
   0.500   0.0543   0.02189   0.01110  -0.0027   0.9861   1.0000
   0.750   0.0847   0.02198   0.01123  -0.0045   0.9783   1.0000
   1.000   0.1160   0.02210   0.01140  -0.0064   0.9706   1.0000
   1.250   0.1454   0.02221   0.01159  -0.0079   0.9616   1.0000
   1.500   0.1784   0.02237   0.01187  -0.0100   0.9534   1.0000
   1.750   0.2120   0.02253   0.01216  -0.0121   0.9441   1.0000
   2.000   0.2442   0.02269   0.01247  -0.0138   0.9335   1.0000
   2.250   0.2833   0.02283   0.01280  -0.0166   0.9223   1.0000
   2.500   0.3315   0.02288   0.01313  -0.0207   0.9087   1.0000
   2.750   0.4044   0.02239   0.01300  -0.0278   0.8845   1.0000
   3.000   0.4531   0.02158   0.01251  -0.0292   0.8442   1.0000
   3.250   0.4786   0.02097   0.01209  -0.0266   0.8035   1.0000
   3.500   0.4946   0.02054   0.01182  -0.0229   0.7641   1.0000
   3.750   0.5056   0.02019   0.01163  -0.0186   0.7154   1.0000
   4.000   0.5148   0.01986   0.01143  -0.0139   0.6392   1.0000
   4.250   0.5286   0.01999   0.01034  -0.0083   0.4074   1.0000
   4.500   0.5286   0.02148   0.01093  -0.0039   0.2732   1.0000
   4.750   0.5334   0.02279   0.01174  -0.0006   0.2070   1.0000
   5.000   0.5418   0.02390   0.01260   0.0023   0.1690   1.0000
   5.250   0.5530   0.02496   0.01350   0.0049   0.1441   1.0000
   5.500   0.5672   0.02602   0.01451   0.0071   0.1254   1.0000
   5.750   0.5837   0.02709   0.01557   0.0088   0.1090   1.0000
   6.000   0.6062   0.02834   0.01694   0.0100   0.0979   1.0000
   6.250   0.6283   0.02964   0.01831   0.0111   0.0860   1.0000
   6.500   0.6523   0.03130   0.01995   0.0119   0.0782   1.0000
   6.750   0.6754   0.03300   0.02196   0.0129   0.0706   1.0000
   7.000   0.6952   0.03481   0.02389   0.0140   0.0644   1.0000
   7.250   0.7161   0.03726   0.02681   0.0153   0.0606   1.0000
   7.500   0.7330   0.03942   0.02923   0.0167   0.0564   1.0000
   7.750   0.7475   0.04165   0.03153   0.0180   0.0526   1.0000
   8.000   0.7579   0.04472   0.03522   0.0202   0.0502   1.0000
   8.250   0.7652   0.04815   0.03915   0.0223   0.0489   1.0000
   8.500   0.7685   0.05175   0.04319   0.0245   0.0480   1.0000
   8.750   0.7685   0.05530   0.04710   0.0265   0.0473   1.0000
   9.000   0.7649   0.05886   0.05098   0.0284   0.0465   1.0000
   9.250   0.7580   0.06240   0.05477   0.0302   0.0457   1.0000
   9.500   0.7481   0.06591   0.05846   0.0317   0.0447   1.0000
   9.750   0.7297   0.06980   0.06249   0.0332   0.0451   1.0000
  10.000   0.7081   0.07438   0.06719   0.0330   0.0458   1.0000
  10.250   0.6860   0.07993   0.07280   0.0309   0.0463   1.0000
  10.500   0.6660   0.08656   0.07945   0.0269   0.0475   1.0000
  10.750   0.6512   0.09406   0.08692   0.0220   0.0487   1.0000
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