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LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-100 (lwk80100-il)
Reynolds number: 500,000
Max Cl/Cd: 49.01 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80100-il-500000.txt
Download as CSV file: xf-lwk80100-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7135   0.09312   0.09094  -0.0086   1.0000   0.0155
 -11.500  -0.7303   0.08654   0.08440  -0.0128   1.0000   0.0145
 -11.250  -0.7737   0.06822   0.06593  -0.0274   1.0000   0.0138
 -11.000  -0.8100   0.05945   0.05697  -0.0323   1.0000   0.0133
 -10.750  -0.9390   0.04052   0.03699  -0.0288   1.0000   0.0114
 -10.500  -0.8805   0.04648   0.04343  -0.0311   1.0000   0.0129
 -10.250  -0.8997   0.04245   0.03912  -0.0274   1.0000   0.0130
 -10.000  -0.9352   0.03404   0.02991  -0.0217   1.0000   0.0121
  -9.750  -0.9319   0.03105   0.02659  -0.0191   1.0000   0.0123
  -9.500  -0.9214   0.02907   0.02439  -0.0172   1.0000   0.0126
  -9.250  -0.9093   0.02703   0.02210  -0.0153   1.0000   0.0128
  -9.000  -0.8944   0.02539   0.02026  -0.0136   1.0000   0.0134
  -8.750  -0.8767   0.02430   0.01901  -0.0123   1.0000   0.0143
  -8.500  -0.8599   0.02263   0.01712  -0.0107   1.0000   0.0146
  -8.250  -0.8418   0.02116   0.01546  -0.0093   1.0000   0.0149
  -8.000  -0.8216   0.02046   0.01461  -0.0081   1.0000   0.0154
  -7.750  -0.8088   0.01796   0.01189  -0.0058   1.0000   0.0162
  -7.500  -0.7896   0.01681   0.01069  -0.0048   0.9915   0.0173
  -7.250  -0.7561   0.01592   0.00974  -0.0066   0.9834   0.0184
  -7.000  -0.7210   0.01521   0.00896  -0.0086   0.9765   0.0206
  -6.750  -0.6863   0.01412   0.00776  -0.0106   0.9701   0.0237
  -6.500  -0.6502   0.01345   0.00706  -0.0129   0.9635   0.0275
  -6.250  -0.6130   0.01281   0.00633  -0.0154   0.9574   0.0317
  -6.000  -0.5786   0.01219   0.00570  -0.0173   0.9494   0.0383
  -5.750  -0.5446   0.01168   0.00514  -0.0190   0.9423   0.0450
  -5.500  -0.5152   0.01139   0.00481  -0.0196   0.9341   0.0524
  -5.250  -0.4871   0.01096   0.00438  -0.0200   0.9272   0.0626
  -5.000  -0.4635   0.01061   0.00405  -0.0194   0.9195   0.0755
  -4.750  -0.4377   0.01029   0.00375  -0.0192   0.9135   0.0938
  -4.500  -0.4161   0.00989   0.00347  -0.0181   0.9071   0.1235
  -4.250  -0.3949   0.00941   0.00320  -0.0171   0.9015   0.1785
  -4.000  -0.3764   0.00878   0.00294  -0.0157   0.8960   0.2686
  -3.750  -0.3603   0.00809   0.00268  -0.0137   0.8902   0.3798
  -3.500  -0.3465   0.00732   0.00244  -0.0112   0.8853   0.5131
  -3.250  -0.3328   0.00681   0.00241  -0.0082   0.8802   0.6381
  -3.000  -0.3102   0.00675   0.00245  -0.0069   0.8759   0.6865
  -2.750  -0.2854   0.00677   0.00249  -0.0061   0.8722   0.7151
  -2.500  -0.2597   0.00682   0.00252  -0.0055   0.8689   0.7326
  -2.250  -0.2346   0.00686   0.00255  -0.0048   0.8648   0.7474
  -2.000  -0.2088   0.00692   0.00259  -0.0042   0.8611   0.7604
  -1.750  -0.1825   0.00698   0.00261  -0.0038   0.8578   0.7704
  -1.500  -0.1561   0.00706   0.00268  -0.0033   0.8547   0.7803
  -1.250  -0.1307   0.00713   0.00277  -0.0026   0.8509   0.7910
  -1.000  -0.1052   0.00721   0.00286  -0.0019   0.8471   0.8018
  -0.750  -0.0789   0.00729   0.00292  -0.0014   0.8437   0.8108
  -0.500  -0.0519   0.00735   0.00300  -0.0011   0.8405   0.8180
  -0.250  -0.0268   0.00738   0.00304  -0.0004   0.8356   0.8253
   0.000   0.0000   0.00738   0.00304   0.0000   0.8308   0.8307
   0.250   0.0269   0.00739   0.00304   0.0004   0.8254   0.8356
   0.500   0.0519   0.00734   0.00299   0.0011   0.8177   0.8404
   0.750   0.0789   0.00729   0.00292   0.0014   0.8107   0.8437
   1.000   0.1052   0.00721   0.00286   0.0019   0.8018   0.8471
   1.250   0.1309   0.00714   0.00278   0.0026   0.7916   0.8509
   1.500   0.1560   0.00705   0.00267   0.0034   0.7794   0.8548
   1.750   0.1825   0.00698   0.00260   0.0038   0.7700   0.8579
   2.000   0.2087   0.00691   0.00258   0.0043   0.7593   0.8611
   2.250   0.2346   0.00686   0.00255   0.0048   0.7469   0.8648
   2.500   0.2597   0.00682   0.00252   0.0055   0.7318   0.8689
   2.750   0.2855   0.00677   0.00249   0.0061   0.7160   0.8722
   3.000   0.3108   0.00675   0.00247   0.0068   0.6915   0.8758
   3.250   0.3333   0.00680   0.00242   0.0081   0.6419   0.8802
   3.500   0.3475   0.00728   0.00243   0.0110   0.5216   0.8853
   3.750   0.3606   0.00807   0.00268   0.0137   0.3819   0.8902
   4.000   0.3762   0.00880   0.00295   0.0157   0.2660   0.8961
   4.250   0.3951   0.00940   0.00320   0.0171   0.1798   0.9015
   4.500   0.4164   0.00988   0.00346   0.0181   0.1251   0.9071
   4.750   0.4381   0.01026   0.00373   0.0191   0.0963   0.9135
   5.000   0.4636   0.01060   0.00405   0.0194   0.0775   0.9196
   5.250   0.4873   0.01094   0.00436   0.0200   0.0644   0.9273
   5.500   0.5155   0.01136   0.00478   0.0196   0.0526   0.9341
   5.750   0.5449   0.01164   0.00509   0.0190   0.0444   0.9422
   6.000   0.5791   0.01211   0.00562   0.0172   0.0378   0.9493
   6.250   0.6126   0.01290   0.00642   0.0154   0.0305   0.9575
   6.500   0.6509   0.01333   0.00692   0.0129   0.0261   0.9633
   6.750   0.6842   0.01463   0.00830   0.0110   0.0217   0.9706
   7.000   0.7217   0.01510   0.00884   0.0085   0.0195   0.9764
   7.250   0.7564   0.01587   0.00967   0.0065   0.0180   0.9834
   7.500   0.7892   0.01692   0.01077   0.0048   0.0165   0.9918
   7.750   0.8054   0.01880   0.01279   0.0064   0.0157   1.0000
   8.000   0.8218   0.02041   0.01457   0.0081   0.0152   1.0000
   8.250   0.8410   0.02147   0.01581   0.0095   0.0149   1.0000
   8.500   0.8591   0.02292   0.01745   0.0110   0.0143   1.0000
   8.750   0.8752   0.02478   0.01954   0.0126   0.0141   1.0000
   9.000   0.8914   0.02625   0.02122   0.0142   0.0135   1.0000
   9.250   0.9056   0.02796   0.02315   0.0159   0.0130   1.0000
   9.500   0.9166   0.03010   0.02554   0.0179   0.0126   1.0000
   9.750   0.9224   0.03291   0.02867   0.0203   0.0125   1.0000
  10.000   0.9239   0.03596   0.03205   0.0229   0.0124   1.0000
  10.250   0.8879   0.04405   0.04083   0.0283   0.0131   1.0000
  10.500   0.8550   0.04954   0.04664   0.0323   0.0138   1.0000
  10.750   0.8301   0.05444   0.05177   0.0333   0.0138   1.0000
  11.000   0.8042   0.06024   0.05776   0.0319   0.0138   1.0000
  11.250   0.7740   0.06795   0.06564   0.0274   0.0142   1.0000
  11.500   0.5486   0.08516   0.08307   0.0195   0.0197   1.0000
  11.750   0.5760   0.08177   0.07970   0.0209   0.0170   1.0000
  12.000   0.5662   0.08758   0.08550   0.0186   0.0167   1.0000
  12.250   0.5650   0.09082   0.08873   0.0173   0.0162   1.0000
  13.250   0.6564   0.14458   0.14224  -0.0147   0.0205   1.0000
  13.500   0.4760   0.12429   0.12215   0.0060   0.0220   1.0000
  13.750   0.4746   0.12797   0.12583   0.0042   0.0220   1.0000
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