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LWK 80-150/K25 (lwk80150k25-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-150/K25 (lwk80150k25-il)
Reynolds number: 100,000
Max Cl/Cd: 38.12 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80150k25-il-100000.txt
Download as CSV file: xf-lwk80150k25-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7319   0.09471   0.08921  -0.0487   1.0000   0.0838
 -13.250  -0.7250   0.08981   0.08433  -0.0492   1.0000   0.0827
 -13.000  -0.7495   0.08270   0.07715  -0.0520   1.0000   0.0817
 -12.750  -0.7781   0.07621   0.07055  -0.0540   1.0000   0.0802
 -12.500  -0.8141   0.07017   0.06433  -0.0548   1.0000   0.0792
 -12.250  -0.8463   0.06507   0.05901  -0.0541   1.0000   0.0777
 -12.000  -0.8768   0.06070   0.05439  -0.0521   1.0000   0.0770
 -11.750  -0.9034   0.05698   0.05040  -0.0490   1.0000   0.0763
 -11.500  -0.9236   0.05395   0.04711  -0.0452   1.0000   0.0761
 -11.250  -0.9371   0.05135   0.04427  -0.0413   1.0000   0.0763
 -11.000  -0.9444   0.04895   0.04166  -0.0377   1.0000   0.0767
 -10.750  -0.9504   0.04728   0.03983  -0.0338   1.0000   0.0779
 -10.500  -0.9634   0.04599   0.03837  -0.0284   1.0000   0.0785
 -10.250  -0.9781   0.04491   0.03712  -0.0224   1.0000   0.0793
 -10.000  -0.9889   0.04370   0.03569  -0.0170   1.0000   0.0805
  -9.750  -0.9958   0.04223   0.03393  -0.0121   1.0000   0.0817
  -9.500  -0.9996   0.04082   0.03216  -0.0075   1.0000   0.0830
  -9.250  -0.9973   0.03914   0.03017  -0.0039   1.0000   0.0841
  -9.000  -0.9797   0.03707   0.02816  -0.0029   1.0000   0.0871
  -8.750  -0.9696   0.03598   0.02699  -0.0005   1.0000   0.0904
  -8.500  -0.9602   0.03486   0.02564   0.0022   1.0000   0.0941
  -8.250  -0.9444   0.03330   0.02390   0.0039   1.0000   0.0979
  -8.000  -0.9278   0.03220   0.02288   0.0053   1.0000   0.1027
  -7.750  -0.9158   0.03133   0.02181   0.0077   1.0000   0.1085
  -7.500  -0.8957   0.02997   0.02056   0.0086   1.0000   0.1149
  -7.250  -0.8821   0.02916   0.01964   0.0107   1.0000   0.1224
  -7.000  -0.8656   0.02807   0.01868   0.0122   1.0000   0.1310
  -6.750  -0.8520   0.02717   0.01777   0.0143   1.0000   0.1419
  -6.500  -0.8395   0.02640   0.01703   0.0165   1.0000   0.1535
  -6.250  -0.8218   0.02549   0.01623   0.0176   0.9987   0.1698
  -6.000  -0.8031   0.02448   0.01548   0.0185   0.9965   0.1914
  -5.750  -0.7859   0.02351   0.01477   0.0195   0.9937   0.2232
  -5.500  -0.7740   0.02230   0.01405   0.0215   0.9907   0.2746
  -5.250  -0.7703   0.02079   0.01338   0.0248   0.9879   0.3780
  -5.000  -0.7671   0.02011   0.01406   0.0302   0.9857   0.5627
  -4.750  -0.7470   0.02130   0.01546   0.0334   0.9828   0.6604
  -4.500  -0.7226   0.02263   0.01669   0.0355   0.9798   0.7003
  -4.250  -0.6987   0.02394   0.01786   0.0375   0.9775   0.7275
  -4.000  -0.6747   0.02528   0.01911   0.0399   0.9752   0.7464
  -3.750  -0.6473   0.02655   0.02027   0.0415   0.9722   0.7636
  -3.500  -0.6165   0.02779   0.02139   0.0424   0.9695   0.7801
  -3.250  -0.5830   0.02895   0.02243   0.0426   0.9672   0.7960
  -3.000  -0.5608   0.02965   0.02303   0.0444   0.9644   0.8112
  -2.750  -0.4898   0.03158   0.02483   0.0390   0.9620   0.8229
  -2.500  -0.4001   0.03333   0.02641   0.0297   0.9606   0.8370
  -2.250  -0.3371   0.03405   0.02702   0.0237   0.9586   0.8499
  -2.000  -0.2983   0.03435   0.02722   0.0214   0.9559   0.8632
  -1.750  -0.2229   0.03473   0.02750   0.0125   0.9541   0.8707
  -1.500  -0.2088   0.03462   0.02735   0.0141   0.9499   0.8815
  -1.250  -0.1678   0.03464   0.02731   0.0109   0.9464   0.8895
  -1.000  -0.1301   0.03463   0.02726   0.0080   0.9426   0.8976
  -0.750  -0.0863   0.03467   0.02726   0.0040   0.9393   0.9044
  -0.500  -0.0758   0.03458   0.02716   0.0060   0.9336   0.9126
  -0.250  -0.0264   0.03456   0.02713   0.0010   0.9294   0.9178
   0.000  -0.0001   0.03465   0.02721   0.0000   0.9242   0.9242
   0.250   0.0279   0.03456   0.02713  -0.0012   0.9179   0.9296
   0.500   0.0751   0.03458   0.02717  -0.0059   0.9127   0.9338
   0.750   0.0851   0.03468   0.02728  -0.0039   0.9047   0.9394
   1.000   0.1302   0.03463   0.02727  -0.0080   0.8977   0.9428
   1.250   0.1680   0.03465   0.02733  -0.0109   0.8898   0.9465
   1.500   0.2090   0.03461   0.02734  -0.0142   0.8815   0.9500
   1.750   0.2232   0.03472   0.02749  -0.0125   0.8706   0.9541
   2.000   0.2974   0.03436   0.02723  -0.0212   0.8633   0.9560
   2.250   0.3399   0.03400   0.02697  -0.0242   0.8498   0.9587
   2.500   0.4064   0.03319   0.02628  -0.0307   0.8366   0.9605
   2.750   0.4909   0.03155   0.02480  -0.0392   0.8229   0.9623
   3.000   0.5565   0.02975   0.02313  -0.0438   0.8103   0.9645
   3.250   0.5855   0.02881   0.02229  -0.0428   0.7957   0.9673
   3.500   0.6181   0.02765   0.02124  -0.0425   0.7796   0.9695
   3.750   0.6478   0.02648   0.02020  -0.0415   0.7634   0.9722
   4.000   0.6750   0.02522   0.01904  -0.0399   0.7461   0.9751
   4.250   0.6988   0.02391   0.01783  -0.0375   0.7274   0.9776
   4.500   0.7229   0.02262   0.01669  -0.0356   0.7004   0.9799
   4.750   0.7473   0.02127   0.01543  -0.0335   0.6601   0.9829
   5.000   0.7670   0.02012   0.01408  -0.0302   0.5643   0.9858
   5.250   0.7701   0.02079   0.01337  -0.0248   0.3768   0.9880
   5.500   0.7738   0.02229   0.01404  -0.0214   0.2750   0.9906
   5.750   0.7858   0.02349   0.01476  -0.0195   0.2233   0.9937
   6.000   0.8032   0.02447   0.01547  -0.0185   0.1920   0.9965
   6.250   0.8221   0.02550   0.01622  -0.0177   0.1706   0.9988
   6.500   0.8395   0.02639   0.01701  -0.0165   0.1539   1.0000
   6.750   0.8519   0.02714   0.01775  -0.0143   0.1420   1.0000
   7.000   0.8660   0.02806   0.01867  -0.0123   0.1317   1.0000
   7.250   0.8830   0.02918   0.01964  -0.0109   0.1230   1.0000
   7.500   0.8955   0.02994   0.02054  -0.0086   0.1151   1.0000
   7.750   0.9154   0.03129   0.02177  -0.0076   0.1086   1.0000
   8.000   0.9270   0.03212   0.02280  -0.0052   0.1028   1.0000
   8.250   0.9441   0.03327   0.02387  -0.0039   0.0979   1.0000
   8.500   0.9599   0.03482   0.02561  -0.0022   0.0941   1.0000
   8.750   0.9688   0.03590   0.02690   0.0006   0.0902   1.0000
   9.000   0.9792   0.03700   0.02807   0.0030   0.0868   1.0000
   9.250   0.9982   0.03932   0.03033   0.0037   0.0839   1.0000
   9.500   0.9980   0.04074   0.03210   0.0078   0.0827   1.0000
   9.750   0.9960   0.04225   0.03393   0.0121   0.0818   1.0000
  10.000   0.9892   0.04374   0.03572   0.0169   0.0806   1.0000
  10.250   0.9782   0.04498   0.03720   0.0224   0.0795   1.0000
  10.500   0.9629   0.04608   0.03848   0.0284   0.0787   1.0000
  10.750   0.9506   0.04722   0.03976   0.0338   0.0775   1.0000
  11.000   0.9455   0.04892   0.04160   0.0376   0.0763   1.0000
  11.250   0.9397   0.05126   0.04415   0.0410   0.0759   1.0000
  11.500   0.9255   0.05391   0.04705   0.0450   0.0759   1.0000
  11.750   0.9031   0.05705   0.05047   0.0490   0.0764   1.0000
  12.000   0.8768   0.06078   0.05447   0.0520   0.0771   1.0000
  12.250   0.8467   0.06515   0.05909   0.0540   0.0779   1.0000
  12.500   0.8122   0.07039   0.06456   0.0547   0.0789   1.0000
  12.750   0.7781   0.07635   0.07069   0.0538   0.0802   1.0000
  13.000   0.7437   0.08345   0.07792   0.0514   0.0815   1.0000
  13.250   0.7234   0.09024   0.08476   0.0487   0.0827   1.0000
  13.500   0.7284   0.09530   0.08980   0.0481   0.0837   1.0000
  13.750   0.4083   0.13023   0.12535   0.0258   0.1564   1.0000
  14.000   0.4055   0.13381   0.12893   0.0244   0.1539   1.0000
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