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LWK 80-150/K25 (lwk80150k25-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-150/K25 (lwk80150k25-il)
Reynolds number: 50,000
Max Cl/Cd: 23.37 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80150k25-il-50000-n5.txt
Download as CSV file: xf-lwk80150k25-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-150/K25                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.6577   0.10552   0.09763  -0.0394   1.0000   0.0704
 -13.500  -0.6992   0.09348   0.08552  -0.0466   1.0000   0.0695
 -13.250  -0.7409   0.08392   0.07581  -0.0517   1.0000   0.0686
 -13.000  -0.7765   0.07674   0.06843  -0.0543   1.0000   0.0683
 -12.750  -0.8036   0.07134   0.06282  -0.0552   1.0000   0.0684
 -12.500  -0.8261   0.06679   0.05802  -0.0551   1.0000   0.0687
 -12.250  -0.8429   0.06303   0.05402  -0.0542   1.0000   0.0692
 -12.000  -0.8582   0.05959   0.05029  -0.0526   1.0000   0.0702
 -11.750  -0.8696   0.05646   0.04684  -0.0507   1.0000   0.0713
 -11.500  -0.8777   0.05356   0.04357  -0.0485   1.0000   0.0724
 -11.250  -0.8664   0.05164   0.04169  -0.0476   1.0000   0.0747
 -11.000  -0.8586   0.04976   0.03970  -0.0462   1.0000   0.0771
 -10.750  -0.8534   0.04784   0.03758  -0.0444   1.0000   0.0800
 -10.500  -0.8463   0.04577   0.03516  -0.0425   1.0000   0.0829
 -10.250  -0.8281   0.04402   0.03338  -0.0419   1.0000   0.0863
 -10.000  -0.8142   0.04266   0.03197  -0.0405   1.0000   0.0903
  -9.750  -0.8001   0.04119   0.03021  -0.0390   1.0000   0.0954
  -9.500  -0.7800   0.03992   0.02903  -0.0383   1.0000   0.1007
  -9.250  -0.7663   0.03891   0.02791  -0.0365   1.0000   0.1068
  -9.000  -0.7471   0.03787   0.02687  -0.0353   1.0000   0.1137
  -8.750  -0.7357   0.03712   0.02604  -0.0330   1.0000   0.1213
  -8.500  -0.7233   0.03640   0.02534  -0.0307   1.0000   0.1291
  -8.250  -0.7166   0.03580   0.02466  -0.0277   1.0000   0.1381
  -8.000  -0.7130   0.03519   0.02414  -0.0243   1.0000   0.1461
  -7.750  -0.7092   0.03460   0.02352  -0.0209   1.0000   0.1564
  -7.500  -0.7094   0.03399   0.02296  -0.0170   1.0000   0.1667
  -7.250  -0.7106   0.03336   0.02239  -0.0129   1.0000   0.1779
  -7.000  -0.6982   0.03238   0.02151  -0.0115   0.9960   0.1982
  -6.750  -0.6841   0.03131   0.02063  -0.0105   0.9903   0.2250
  -6.500  -0.6720   0.03021   0.01978  -0.0093   0.9846   0.2610
  -6.250  -0.6622   0.02907   0.01898  -0.0076   0.9791   0.3104
  -6.000  -0.6555   0.02806   0.01844  -0.0049   0.9737   0.3763
  -5.750  -0.6303   0.02807   0.01926  -0.0031   0.9707   0.4823
  -5.500  -0.5815   0.02994   0.02137  -0.0031   0.9695   0.5717
  -5.250  -0.5584   0.03073   0.02201  -0.0015   0.9652   0.6158
  -5.000  -0.5435   0.03130   0.02241   0.0011   0.9599   0.6479
  -4.750  -0.5259   0.03185   0.02278   0.0031   0.9556   0.6766
  -4.500  -0.4957   0.03299   0.02373   0.0041   0.9525   0.6985
  -4.250  -0.4715   0.03384   0.02441   0.0058   0.9484   0.7194
  -4.000  -0.4439   0.03455   0.02497   0.0066   0.9449   0.7390
  -3.750  -0.4067   0.03531   0.02553   0.0059   0.9426   0.7555
  -3.500  -0.3647   0.03592   0.02598   0.0041   0.9409   0.7697
  -3.250  -0.3413   0.03616   0.02609   0.0050   0.9368   0.7828
  -3.000  -0.3222   0.03623   0.02604   0.0062   0.9324   0.7962
  -2.750  -0.2787   0.03638   0.02605   0.0033   0.9302   0.8050
  -2.500  -0.2490   0.03634   0.02589   0.0024   0.9272   0.8151
  -2.250  -0.2202   0.03633   0.02578   0.0017   0.9237   0.8238
  -2.000  -0.2015   0.03625   0.02564   0.0027   0.9189   0.8325
  -1.750  -0.1705   0.03621   0.02551   0.0015   0.9154   0.8401
  -1.500  -0.1440   0.03612   0.02535   0.0009   0.9120   0.8479
  -1.250  -0.1104   0.03607   0.02525  -0.0009   0.9085   0.8536
  -1.000  -0.1089   0.03600   0.02514   0.0030   0.9019   0.8629
  -0.750  -0.0686   0.03596   0.02506  -0.0001   0.8986   0.8670
  -0.500  -0.0336   0.03591   0.02499  -0.0022   0.8954   0.8720
  -0.250  -0.0340   0.03590   0.02497   0.0020   0.8882   0.8799
   0.000   0.0001   0.03589   0.02495   0.0000   0.8837   0.8838
   0.250   0.0343   0.03589   0.02496  -0.0020   0.8799   0.8883
   0.500   0.0335   0.03591   0.02499   0.0023   0.8720   0.8954
   0.750   0.0695   0.03595   0.02506  -0.0001   0.8669   0.8987
   1.000   0.1097   0.03599   0.02514  -0.0031   0.8628   0.9019
   1.250   0.1108   0.03607   0.02524   0.0008   0.8535   0.9085
   1.500   0.1433   0.03612   0.02535  -0.0008   0.8479   0.9120
   1.750   0.1703   0.03621   0.02551  -0.0015   0.8404   0.9155
   2.000   0.2008   0.03627   0.02565  -0.0026   0.8326   0.9191
   2.250   0.2203   0.03633   0.02578  -0.0018   0.8240   0.9238
   2.500   0.2496   0.03634   0.02589  -0.0025   0.8151   0.9273
   2.750   0.2793   0.03637   0.02604  -0.0034   0.8050   0.9303
   3.000   0.3229   0.03620   0.02602  -0.0063   0.7962   0.9324
   3.250   0.3417   0.03614   0.02607  -0.0050   0.7828   0.9368
   3.500   0.3650   0.03589   0.02595  -0.0041   0.7695   0.9409
   3.750   0.4070   0.03529   0.02552  -0.0059   0.7555   0.9427
   4.000   0.4445   0.03454   0.02496  -0.0067   0.7392   0.9449
   4.250   0.4719   0.03383   0.02441  -0.0059   0.7197   0.9485
   4.500   0.4953   0.03303   0.02376  -0.0041   0.6990   0.9526
   5.000   0.5436   0.03130   0.02242  -0.0012   0.6482   0.9600
   5.250   0.5587   0.03071   0.02199   0.0015   0.6155   0.9653
   5.500   0.5819   0.02993   0.02137   0.0031   0.5719   0.9695
   5.750   0.6307   0.02805   0.01923   0.0031   0.4818   0.9707
   6.000   0.6556   0.02805   0.01843   0.0049   0.3764   0.9737
   6.250   0.6626   0.02905   0.01896   0.0075   0.3111   0.9791
   6.500   0.6723   0.03020   0.01977   0.0092   0.2611   0.9847
   6.750   0.6843   0.03130   0.02062   0.0104   0.2253   0.9903
   7.000   0.6986   0.03236   0.02150   0.0114   0.1985   0.9960
   7.250   0.7112   0.03333   0.02237   0.0128   0.1786   1.0000
   7.500   0.7100   0.03398   0.02295   0.0169   0.1672   1.0000
   7.750   0.7100   0.03458   0.02351   0.0208   0.1566   1.0000
   8.000   0.7132   0.03516   0.02411   0.0243   0.1465   1.0000
   8.250   0.7175   0.03579   0.02464   0.0276   0.1385   1.0000
   8.500   0.7245   0.03638   0.02533   0.0306   0.1295   1.0000
   8.750   0.7374   0.03712   0.02603   0.0328   0.1216   1.0000
   9.000   0.7469   0.03785   0.02684   0.0353   0.1138   1.0000
   9.250   0.7649   0.03884   0.02783   0.0366   0.1072   1.0000
   9.500   0.7792   0.03987   0.02898   0.0384   0.1008   1.0000
   9.750   0.8007   0.04117   0.03018   0.0389   0.0956   1.0000
  10.000   0.8152   0.04267   0.03198   0.0404   0.0904   1.0000
  10.250   0.8284   0.04401   0.03337   0.0418   0.0863   1.0000
  10.500   0.8455   0.04576   0.03517   0.0426   0.0827   1.0000
  10.750   0.8520   0.04777   0.03750   0.0445   0.0796   1.0000
  11.000   0.8584   0.04970   0.03963   0.0462   0.0767   1.0000
  11.250   0.8670   0.05148   0.04148   0.0475   0.0743   1.0000
  11.500   0.8771   0.05357   0.04359   0.0485   0.0723   1.0000
  11.750   0.8687   0.05646   0.04686   0.0507   0.0711   1.0000
  12.000   0.8585   0.05959   0.05029   0.0526   0.0701   1.0000
  12.250   0.8436   0.06300   0.05399   0.0541   0.0691   1.0000
  12.500   0.8256   0.06682   0.05806   0.0550   0.0681   1.0000
  12.750   0.8044   0.07126   0.06273   0.0551   0.0679   1.0000
  13.000   0.7767   0.07674   0.06843   0.0542   0.0678   1.0000
  13.250   0.7408   0.08403   0.07592   0.0515   0.0683   1.0000
  13.500   0.6972   0.09398   0.08601   0.0461   0.0692   1.0000
  13.750   0.6562   0.10610   0.09820   0.0388   0.0702   1.0000
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