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LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-100 (lwk80100-il)
Reynolds number: 500,000
Max Cl/Cd: 51.13 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80100-il-500000-n5.txt
Download as CSV file: xf-lwk80100-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.9708   0.06713   0.06455  -0.0218   1.0000   0.0057
 -13.500  -0.9974   0.05807   0.05528  -0.0283   1.0000   0.0057
 -13.250  -1.0211   0.05138   0.04836  -0.0316   1.0000   0.0057
 -13.000  -1.0431   0.04583   0.04254  -0.0328   1.0000   0.0056
 -12.750  -1.0522   0.04235   0.03886  -0.0328   1.0000   0.0057
 -12.500  -1.0552   0.03973   0.03605  -0.0322   1.0000   0.0059
 -12.250  -1.0602   0.03700   0.03310  -0.0310   1.0000   0.0060
 -12.000  -1.0642   0.03444   0.03032  -0.0292   1.0000   0.0060
 -11.750  -1.0641   0.03236   0.02802  -0.0271   1.0000   0.0062
 -11.500  -1.0613   0.03055   0.02600  -0.0247   1.0000   0.0063
 -11.250  -1.0554   0.02900   0.02427  -0.0224   1.0000   0.0063
 -11.000  -1.0466   0.02736   0.02241  -0.0204   1.0000   0.0065
 -10.750  -1.0354   0.02584   0.02069  -0.0186   1.0000   0.0067
 -10.500  -1.0200   0.02477   0.01946  -0.0172   1.0000   0.0070
 -10.250  -1.0023   0.02398   0.01853  -0.0161   1.0000   0.0072
 -10.000  -0.9882   0.02262   0.01701  -0.0144   1.0000   0.0072
  -9.750  -0.9749   0.02115   0.01540  -0.0126   1.0000   0.0077
  -9.500  -0.9566   0.02036   0.01451  -0.0115   1.0000   0.0081
  -9.250  -0.9383   0.01952   0.01358  -0.0102   1.0000   0.0084
  -9.000  -0.9186   0.01885   0.01284  -0.0092   1.0000   0.0089
  -8.750  -0.8996   0.01809   0.01199  -0.0079   1.0000   0.0094
  -8.500  -0.8674   0.01717   0.01095  -0.0096   0.9725   0.0098
  -8.250  -0.8297   0.01629   0.00994  -0.0124   0.9578   0.0102
  -8.000  -0.7918   0.01544   0.00895  -0.0153   0.9458   0.0111
  -7.750  -0.7550   0.01468   0.00812  -0.0179   0.9343   0.0123
  -7.500  -0.7207   0.01419   0.00756  -0.0199   0.9227   0.0139
  -7.250  -0.6908   0.01376   0.00701  -0.0207   0.9116   0.0152
  -7.000  -0.6653   0.01327   0.00647  -0.0206   0.9013   0.0178
  -6.750  -0.6405   0.01292   0.00605  -0.0203   0.8931   0.0203
  -6.500  -0.6157   0.01263   0.00567  -0.0199   0.8861   0.0220
  -6.250  -0.5926   0.01224   0.00527  -0.0192   0.8798   0.0258
  -6.000  -0.5684   0.01199   0.00497  -0.0186   0.8738   0.0296
  -5.750  -0.5445   0.01169   0.00464  -0.0180   0.8685   0.0341
  -5.500  -0.5207   0.01142   0.00436  -0.0173   0.8633   0.0397
  -5.250  -0.4967   0.01116   0.00408  -0.0167   0.8588   0.0459
  -5.000  -0.4722   0.01093   0.00383  -0.0162   0.8550   0.0530
  -4.750  -0.4485   0.01066   0.00359  -0.0155   0.8505   0.0632
  -4.500  -0.4243   0.01042   0.00335  -0.0149   0.8462   0.0736
  -4.250  -0.4000   0.01018   0.00313  -0.0143   0.8427   0.0885
  -4.000  -0.3761   0.00991   0.00293  -0.0137   0.8392   0.1098
  -3.750  -0.3526   0.00961   0.00273  -0.0130   0.8354   0.1376
  -3.250  -0.3080   0.00884   0.00232  -0.0112   0.8283   0.2420
  -3.000  -0.2868   0.00837   0.00213  -0.0101   0.8250   0.3144
  -2.750  -0.2678   0.00780   0.00192  -0.0086   0.8212   0.4107
  -2.500  -0.2491   0.00727   0.00174  -0.0070   0.8175   0.5032
  -2.250  -0.2314   0.00679   0.00164  -0.0049   0.8143   0.6067
  -2.000  -0.2088   0.00663   0.00166  -0.0037   0.8113   0.6643
  -1.750  -0.1834   0.00658   0.00166  -0.0031   0.8079   0.6885
  -1.500  -0.1576   0.00656   0.00167  -0.0026   0.8046   0.7095
  -1.250  -0.1319   0.00655   0.00169  -0.0020   0.8015   0.7292
  -1.000  -0.1059   0.00657   0.00172  -0.0015   0.7988   0.7459
  -0.750  -0.0796   0.00658   0.00175  -0.0011   0.7954   0.7577
  -0.500  -0.0533   0.00660   0.00178  -0.0007   0.7916   0.7683
  -0.250  -0.0266   0.00661   0.00181  -0.0003   0.7878   0.7761
   0.000   0.0001   0.00664   0.00180   0.0000   0.7835   0.7834
   0.250   0.0267   0.00661   0.00181   0.0003   0.7763   0.7878
   0.500   0.0533   0.00660   0.00178   0.0007   0.7678   0.7916
   0.750   0.0796   0.00658   0.00175   0.0011   0.7575   0.7954
   1.000   0.1059   0.00657   0.00172   0.0015   0.7457   0.7987
   1.250   0.1321   0.00655   0.00170   0.0020   0.7302   0.8016
   1.500   0.1575   0.00656   0.00166   0.0026   0.7075   0.8046
   1.750   0.1834   0.00658   0.00166   0.0031   0.6874   0.8079
   2.000   0.2085   0.00664   0.00165   0.0038   0.6594   0.8113
   2.250   0.2311   0.00681   0.00164   0.0050   0.6028   0.8143
   2.500   0.2482   0.00732   0.00175   0.0071   0.4938   0.8175
   2.750   0.2679   0.00780   0.00192   0.0086   0.4109   0.8212
   3.000   0.2883   0.00827   0.00211   0.0099   0.3323   0.8249
   3.250   0.3085   0.00880   0.00231   0.0111   0.2486   0.8283
   3.500   0.3301   0.00924   0.00253   0.0121   0.1839   0.8317
   3.750   0.3528   0.00960   0.00273   0.0130   0.1391   0.8354
   4.000   0.3760   0.00992   0.00293   0.0137   0.1088   0.8393
   4.250   0.4001   0.01018   0.00313   0.0143   0.0896   0.8427
   4.500   0.4244   0.01041   0.00336   0.0149   0.0751   0.8463
   4.750   0.4486   0.01065   0.00358   0.0155   0.0645   0.8506
   5.000   0.4725   0.01091   0.00382   0.0161   0.0548   0.8550
   5.250   0.4970   0.01114   0.00407   0.0167   0.0469   0.8588
   5.500   0.5209   0.01141   0.00434   0.0173   0.0398   0.8633
   5.750   0.5445   0.01169   0.00463   0.0180   0.0330   0.8685
   6.000   0.5686   0.01195   0.00493   0.0186   0.0288   0.8737
   6.250   0.5926   0.01224   0.00525   0.0192   0.0251   0.8797
   6.500   0.6160   0.01260   0.00564   0.0198   0.0215   0.8861
   6.750   0.6406   0.01290   0.00602   0.0203   0.0190   0.8931
   7.000   0.6650   0.01330   0.00648   0.0207   0.0165   0.9014
   7.250   0.6910   0.01374   0.00699   0.0207   0.0148   0.9116
   7.500   0.7210   0.01416   0.00751   0.0198   0.0128   0.9227
   7.750   0.7547   0.01476   0.00817   0.0180   0.0115   0.9345
   8.000   0.7909   0.01565   0.00917   0.0154   0.0105   0.9464
   8.250   0.8293   0.01642   0.01008   0.0125   0.0100   0.9581
   8.500   0.8673   0.01725   0.01104   0.0096   0.0093   0.9730
   8.750   0.8993   0.01814   0.01204   0.0080   0.0089   1.0000
   9.000   0.9187   0.01884   0.01281   0.0092   0.0085   1.0000
   9.250   0.9375   0.01962   0.01368   0.0104   0.0082   1.0000
   9.500   0.9557   0.02046   0.01461   0.0116   0.0079   1.0000
   9.750   0.9729   0.02144   0.01571   0.0130   0.0077   1.0000
  10.000   0.9859   0.02295   0.01737   0.0148   0.0072   1.0000
  10.250   1.0012   0.02417   0.01875   0.0163   0.0071   1.0000
  10.500   1.0163   0.02533   0.02007   0.0177   0.0069   1.0000
  10.750   1.0313   0.02642   0.02133   0.0191   0.0067   1.0000
  11.000   1.0431   0.02782   0.02292   0.0208   0.0066   1.0000
  11.250   1.0515   0.02946   0.02478   0.0228   0.0064   1.0000
  11.500   1.0554   0.03122   0.02674   0.0254   0.0062   1.0000
  11.750   1.0566   0.03318   0.02892   0.0278   0.0062   1.0000
  12.000   1.0589   0.03504   0.03097   0.0296   0.0061   1.0000
  12.250   1.0546   0.03763   0.03379   0.0313   0.0060   1.0000
  12.500   1.0436   0.04107   0.03749   0.0325   0.0060   1.0000
  12.750   1.0420   0.04358   0.04016   0.0329   0.0058   1.0000
  13.000   1.0247   0.04823   0.04506   0.0325   0.0058   1.0000
  13.250   1.0166   0.05210   0.04910   0.0312   0.0056   1.0000
  13.500   0.9643   0.06415   0.06152   0.0241   0.0060   1.0000
  13.750   0.9455   0.07347   0.07102   0.0167   0.0060   1.0000
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