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LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-080 (lwk80080-il)
Reynolds number: 1,000,000
Max Cl/Cd: 54.09 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80080-il-1000000.txt
Download as CSV file: xf-lwk80080-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7286   0.03517   0.03353  -0.0267   1.0000   0.0047
  -9.250  -0.7532   0.03059   0.02879  -0.0242   1.0000   0.0048
  -9.000  -0.8617   0.03551   0.03293  -0.0143   1.0000   0.0044
  -8.750  -0.8693   0.02968   0.02661  -0.0114   1.0000   0.0048
  -8.500  -0.8418   0.03112   0.02815  -0.0118   1.0000   0.0052
  -8.250  -0.8474   0.02390   0.02018  -0.0077   1.0000   0.0051
  -8.000  -0.8279   0.02287   0.01901  -0.0068   1.0000   0.0054
  -7.750  -0.8019   0.02360   0.01982  -0.0069   1.0000   0.0061
  -7.500  -0.7892   0.02030   0.01610  -0.0045   1.0000   0.0061
  -7.250  -0.7716   0.01821   0.01371  -0.0029   1.0000   0.0062
  -7.000  -0.7515   0.01683   0.01214  -0.0015   1.0000   0.0067
  -6.750  -0.7301   0.01587   0.01105  -0.0004   1.0000   0.0072
  -6.500  -0.7089   0.01508   0.01015   0.0008   1.0000   0.0074
  -6.250  -0.6874   0.01313   0.00798   0.0016   0.9911   0.0084
  -6.000  -0.6545   0.01227   0.00706   0.0001   0.9823   0.0096
  -5.750  -0.6200   0.01153   0.00623  -0.0017   0.9725   0.0102
  -5.500  -0.5826   0.01083   0.00541  -0.0041   0.9647   0.0108
  -5.250  -0.5425   0.01022   0.00473  -0.0071   0.9580   0.0115
  -5.000  -0.5033   0.00956   0.00394  -0.0099   0.9494   0.0119
  -4.750  -0.4658   0.00884   0.00310  -0.0122   0.9395   0.0172
  -4.500  -0.4313   0.00852   0.00274  -0.0139   0.9290   0.0243
  -4.250  -0.4010   0.00829   0.00249  -0.0146   0.9185   0.0324
  -4.000  -0.3728   0.00806   0.00226  -0.0149   0.9094   0.0453
  -3.750  -0.3463   0.00784   0.00207  -0.0147   0.9013   0.0632
  -3.500  -0.3217   0.00757   0.00190  -0.0142   0.8938   0.0940
  -3.250  -0.2987   0.00716   0.00171  -0.0134   0.8870   0.1572
  -3.000  -0.2759   0.00682   0.00154  -0.0126   0.8808   0.2159
  -2.750  -0.2590   0.00606   0.00133  -0.0107   0.8744   0.3703
  -2.500  -0.2424   0.00537   0.00115  -0.0086   0.8685   0.5153
  -2.250  -0.2254   0.00488   0.00106  -0.0064   0.8626   0.6356
  -2.000  -0.2026   0.00474   0.00105  -0.0052   0.8579   0.6936
  -1.750  -0.1788   0.00467   0.00106  -0.0042   0.8531   0.7244
  -1.500  -0.1532   0.00465   0.00104  -0.0037   0.8486   0.7418
  -1.250  -0.1268   0.00466   0.00103  -0.0033   0.8445   0.7560
  -1.000  -0.1010   0.00464   0.00103  -0.0028   0.8397   0.7667
  -0.750  -0.0757   0.00464   0.00104  -0.0021   0.8339   0.7802
  -0.500  -0.0503   0.00465   0.00105  -0.0014   0.8270   0.7917
  -0.250  -0.0257   0.00467   0.00105  -0.0006   0.8187   0.8032
   0.000   0.0000   0.00465   0.00105   0.0000   0.8111   0.8109
   0.250   0.0254   0.00467   0.00104   0.0007   0.8023   0.8189
   0.500   0.0503   0.00465   0.00104   0.0015   0.7916   0.8270
   0.750   0.0755   0.00464   0.00104   0.0021   0.7794   0.8340
   1.000   0.1011   0.00464   0.00104   0.0027   0.7674   0.8396
   1.250   0.1266   0.00466   0.00103   0.0033   0.7544   0.8444
   1.500   0.1531   0.00465   0.00104   0.0037   0.7410   0.8486
   1.750   0.1780   0.00468   0.00104   0.0044   0.7189   0.8532
   2.000   0.2018   0.00476   0.00105   0.0054   0.6850   0.8580
   2.250   0.2250   0.00490   0.00106   0.0064   0.6313   0.8626
   2.500   0.2409   0.00547   0.00116   0.0089   0.4952   0.8685
   2.750   0.2584   0.00609   0.00134   0.0108   0.3626   0.8743
   3.000   0.2752   0.00687   0.00157   0.0127   0.2054   0.8808
   3.250   0.2962   0.00737   0.00175   0.0138   0.1195   0.8875
   3.500   0.3209   0.00763   0.00191   0.0143   0.0831   0.8941
   3.750   0.3462   0.00785   0.00207   0.0148   0.0617   0.9013
   4.000   0.3728   0.00807   0.00225   0.0149   0.0434   0.9093
   4.250   0.4010   0.00828   0.00249   0.0146   0.0318   0.9183
   4.500   0.4310   0.00856   0.00277   0.0140   0.0213   0.9289
   4.750   0.4647   0.00909   0.00337   0.0125   0.0125   0.9401
   5.000   0.5035   0.00959   0.00398   0.0099   0.0116   0.9496
   5.250   0.5431   0.01021   0.00471   0.0070   0.0112   0.9581
   5.500   0.5828   0.01087   0.00546   0.0040   0.0104   0.9649
   5.750   0.6204   0.01147   0.00616   0.0015   0.0099   0.9726
   6.000   0.6545   0.01231   0.00709  -0.0001   0.0093   0.9823
   6.250   0.6873   0.01320   0.00807  -0.0016   0.0087   0.9912
   6.500   0.7050   0.01629   0.01149   0.0001   0.0075   1.0000
   6.750   0.7274   0.01680   0.01210   0.0010   0.0072   1.0000
   7.000   0.7482   0.01791   0.01335   0.0022   0.0069   1.0000
   7.250   0.7679   0.01943   0.01508   0.0036   0.0065   1.0000
   7.500   0.7851   0.02157   0.01753   0.0053   0.0064   1.0000
   7.750   0.8045   0.02288   0.01901   0.0064   0.0060   1.0000
   8.000   0.8176   0.02578   0.02226   0.0084   0.0058   1.0000
   8.250   0.8424   0.02531   0.02174   0.0084   0.0053   1.0000
   8.500   0.8510   0.02886   0.02569   0.0106   0.0051   1.0000
   8.750   0.8584   0.03235   0.02951   0.0126   0.0050   1.0000
  10.750   0.6682   0.11161   0.11002  -0.0142   0.0076   1.0000
  11.000   0.6694   0.11601   0.11443  -0.0163   0.0076   1.0000
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