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


Details Polar file
Airfoil: LWK 80-100 (lwk80100-il)
Reynolds number: 100,000
Max Cl/Cd: 59.44 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80100-il-100000.txt
Download as CSV file: xf-lwk80100-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6061   0.12033   0.11520  -0.0030   1.0000   0.1132
 -11.000  -0.6140   0.11602   0.11094  -0.0063   1.0000   0.1187
 -10.750  -0.6507   0.11028   0.10539  -0.0159   1.0000   0.1207
 -10.500  -0.6122   0.10706   0.10205  -0.0085   1.0000   0.1260
 -10.250  -0.6146   0.10289   0.09791  -0.0105   1.0000   0.1308
 -10.000  -0.6611   0.09591   0.09110  -0.0219   1.0000   0.1345
  -9.750  -0.6297   0.09293   0.08809  -0.0158   1.0000   0.1388
  -9.500  -0.6298   0.08886   0.08405  -0.0170   1.0000   0.1436
  -9.250  -0.6759   0.08240   0.07767  -0.0249   1.0000   0.1478
  -9.000  -0.7412   0.08023   0.07536  -0.0251   1.0000   0.1491
  -8.250  -0.7605   0.05431   0.04847  -0.0242   1.0000   0.0822
  -8.000  -0.7663   0.04728   0.04052  -0.0201   1.0000   0.0647
  -7.750  -0.7590   0.04306   0.03603  -0.0180   1.0000   0.0632
  -7.500  -0.7507   0.03938   0.03196  -0.0154   1.0000   0.0623
  -7.250  -0.7402   0.03620   0.02835  -0.0128   1.0000   0.0624
  -7.000  -0.7292   0.03430   0.02588  -0.0097   1.0000   0.0654
  -6.750  -0.7160   0.03115   0.02247  -0.0077   1.0000   0.0685
  -6.500  -0.6995   0.02911   0.02027  -0.0058   1.0000   0.0713
  -6.250  -0.6842   0.02753   0.01844  -0.0034   1.0000   0.0761
  -6.000  -0.6688   0.02577   0.01650  -0.0012   1.0000   0.0822
  -5.750  -0.6521   0.02440   0.01504   0.0009   1.0000   0.0887
  -5.500  -0.6353   0.02301   0.01359   0.0028   1.0000   0.0971
  -5.250  -0.6194   0.02214   0.01255   0.0050   1.0000   0.1069
  -5.000  -0.6025   0.02080   0.01134   0.0069   1.0000   0.1180
  -4.750  -0.5878   0.01988   0.01044   0.0091   1.0000   0.1349
  -4.500  -0.5750   0.01874   0.00954   0.0116   1.0000   0.1536
  -4.250  -0.5633   0.01773   0.00877   0.0142   1.0000   0.1865
  -4.000  -0.5569   0.01618   0.00796   0.0176   1.0000   0.2750
  -3.750  -0.5661   0.01422   0.00815   0.0253   1.0000   0.6259
  -3.500  -0.5596   0.01479   0.00890   0.0315   1.0000   0.7520
  -3.250  -0.5491   0.01531   0.00932   0.0364   1.0000   0.7997
  -3.000  -0.5348   0.01577   0.00969   0.0406   1.0000   0.8331
  -2.750  -0.5179   0.01619   0.01001   0.0444   1.0000   0.8646
  -2.500  -0.4896   0.01668   0.01036   0.0460   1.0000   0.8930
  -2.250  -0.4234   0.01770   0.01112   0.0407   1.0000   0.9204
  -2.000  -0.2469   0.01945   0.01239   0.0157   1.0000   0.9516
  -1.750  -0.1853   0.01938   0.01216   0.0088   1.0000   0.9646
  -1.500  -0.1380   0.01920   0.01187   0.0040   1.0000   0.9748
  -1.250  -0.0951   0.01901   0.01160  -0.0001   1.0000   0.9838
  -1.000  -0.0524   0.01880   0.01133  -0.0043   1.0000   0.9919
  -0.750  -0.0099   0.01862   0.01111  -0.0085   1.0000   0.9992
  -0.500  -0.0033   0.01864   0.01111  -0.0063   1.0000   1.0000
  -0.250  -0.0017   0.01866   0.01113  -0.0031   1.0000   1.0000
   0.000   0.0001   0.01866   0.01114   0.0000   1.0000   1.0000
   0.250   0.0019   0.01866   0.01113   0.0032   1.0000   1.0000
   0.500   0.0034   0.01864   0.01112   0.0063   1.0000   1.0000
   0.750   0.0106   0.01862   0.01111   0.0084   0.9991   1.0000
   1.000   0.0527   0.01880   0.01134   0.0043   0.9919   1.0000
   1.250   0.0953   0.01901   0.01159   0.0001   0.9838   1.0000
   1.500   0.1381   0.01919   0.01187  -0.0040   0.9748   1.0000
   1.750   0.1870   0.01937   0.01216  -0.0090   0.9642   1.0000
   2.000   0.2496   0.01943   0.01237  -0.0161   0.9509   1.0000
   2.250   0.4305   0.01756   0.01099  -0.0417   0.9187   1.0000
   2.500   0.4897   0.01669   0.01038  -0.0460   0.8933   1.0000
   2.750   0.5182   0.01620   0.01002  -0.0445   0.8651   1.0000
   3.000   0.5352   0.01580   0.00973  -0.0408   0.8347   1.0000
   3.250   0.5493   0.01530   0.00931  -0.0364   0.7993   1.0000
   3.500   0.5603   0.01479   0.00891  -0.0316   0.7536   1.0000
   3.750   0.5670   0.01424   0.00823  -0.0256   0.6378   1.0000
   4.000   0.5578   0.01609   0.00794  -0.0178   0.2832   1.0000
   4.250   0.5637   0.01768   0.00873  -0.0143   0.1908   1.0000
   4.500   0.5755   0.01868   0.00951  -0.0116   0.1564   1.0000
   4.750   0.5883   0.01975   0.01038  -0.0091   0.1362   1.0000
   5.000   0.6028   0.02080   0.01132  -0.0069   0.1196   1.0000
   5.250   0.6192   0.02203   0.01248  -0.0050   0.1072   1.0000
   5.500   0.6353   0.02299   0.01358  -0.0028   0.0969   1.0000
   5.750   0.6520   0.02439   0.01505  -0.0008   0.0880   1.0000
   6.000   0.6683   0.02576   0.01643   0.0012   0.0811   1.0000
   6.250   0.6633   0.01116   0.00289   0.0046   0.0736   1.0000
   6.500   0.6755   0.01287   0.00482   0.0072   0.0704   1.0000
   6.750   0.6866   0.01477   0.00679   0.0095   0.0674   1.0000
   7.000   0.6926   0.01718   0.00959   0.0127   0.0646   1.0000
   7.250   0.6996   0.01951   0.01235   0.0158   0.0630   1.0000
   7.500   0.7054   0.02274   0.01598   0.0188   0.0628   1.0000
   7.750   0.7103   0.02647   0.02005   0.0213   0.0637   1.0000
   8.000   0.7140   0.03085   0.02467   0.0235   0.0649   1.0000
   8.250   0.6959   0.03732   0.03197   0.0280   0.0742   1.0000
   9.250   0.6662   0.08251   0.07777   0.0241   0.1473   1.0000
   9.500   0.6291   0.08900   0.08417   0.0169   0.1421   1.0000
   9.750   0.6373   0.09238   0.08755   0.0174   0.1377   1.0000
  10.000   0.6581   0.09605   0.09124   0.0212   0.1344   1.0000
  10.250   0.6124   0.10314   0.09816   0.0099   0.1290   1.0000
  10.500   0.6166   0.10686   0.10185   0.0094   0.1245   1.0000
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