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


Details Polar file
Airfoil: LWK 80-100 (lwk80100-il)
Reynolds number: 100,000
Max Cl/Cd: 31.93 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80100-il-100000-n5.txt
Download as CSV file: xf-lwk80100-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7186   0.07712   0.07195  -0.0304   1.0000   0.0219
 -11.000  -0.7397   0.07066   0.06538  -0.0342   1.0000   0.0218
 -10.750  -0.7620   0.06529   0.05986  -0.0362   1.0000   0.0218
 -10.500  -0.7845   0.06080   0.05521  -0.0364   1.0000   0.0221
 -10.250  -0.8003   0.05738   0.05165  -0.0350   1.0000   0.0223
  -9.750  -0.8200   0.05167   0.04561  -0.0304   1.0000   0.0229
  -9.500  -0.8205   0.04936   0.04313  -0.0285   1.0000   0.0236
  -9.250  -0.8199   0.04677   0.04032  -0.0264   1.0000   0.0242
  -9.000  -0.8167   0.04415   0.03743  -0.0243   1.0000   0.0252
  -8.750  -0.8135   0.04086   0.03369  -0.0219   1.0000   0.0258
  -8.500  -0.8059   0.03789   0.03032  -0.0197   1.0000   0.0265
  -8.250  -0.7947   0.03509   0.02710  -0.0176   1.0000   0.0273
  -8.000  -0.7802   0.03253   0.02413  -0.0158   1.0000   0.0286
  -7.750  -0.7628   0.03048   0.02165  -0.0142   1.0000   0.0303
  -7.500  -0.7463   0.02877   0.01990  -0.0129   1.0000   0.0327
  -7.250  -0.7285   0.02757   0.01859  -0.0116   1.0000   0.0355
  -7.000  -0.7092   0.02607   0.01689  -0.0101   1.0000   0.0384
  -6.750  -0.6908   0.02474   0.01539  -0.0085   1.0000   0.0422
  -6.500  -0.6751   0.02379   0.01443  -0.0068   1.0000   0.0462
  -6.250  -0.6594   0.02281   0.01335  -0.0048   1.0000   0.0506
  -6.000  -0.6467   0.02191   0.01241  -0.0024   1.0000   0.0553
  -5.750  -0.6354   0.02127   0.01176   0.0003   1.0000   0.0615
  -5.500  -0.6246   0.02058   0.01096   0.0032   1.0000   0.0668
  -5.250  -0.6014   0.01976   0.01014   0.0033   0.9946   0.0766
  -5.000  -0.5729   0.01893   0.00927   0.0025   0.9885   0.0902
  -4.750  -0.5444   0.01816   0.00852   0.0018   0.9825   0.1084
  -4.500  -0.5172   0.01737   0.00790   0.0012   0.9765   0.1395
  -4.250  -0.4902   0.01648   0.00732   0.0006   0.9712   0.1999
  -4.000  -0.4686   0.01534   0.00679   0.0008   0.9653   0.3226
  -3.750  -0.4509   0.01411   0.00656   0.0023   0.9594   0.5144
  -3.500  -0.4229   0.01406   0.00708   0.0034   0.9563   0.6663
  -3.250  -0.3980   0.01425   0.00724   0.0046   0.9505   0.7177
  -3.000  -0.3694   0.01446   0.00731   0.0049   0.9461   0.7522
  -2.750  -0.3382   0.01472   0.00748   0.0048   0.9428   0.7796
  -2.500  -0.3121   0.01501   0.00771   0.0059   0.9379   0.8033
  -2.250  -0.2863   0.01528   0.00791   0.0071   0.9333   0.8266
  -2.000  -0.2533   0.01552   0.00807   0.0069   0.9304   0.8435
  -1.750  -0.2196   0.01562   0.00808   0.0060   0.9277   0.8562
  -1.500  -0.1889   0.01571   0.00810   0.0056   0.9232   0.8643
  -1.250  -0.1596   0.01570   0.00803   0.0052   0.9188   0.8724
  -1.000  -0.1234   0.01571   0.00796   0.0035   0.9157   0.8777
  -0.750  -0.0958   0.01567   0.00787   0.0032   0.9113   0.8848
  -0.500  -0.0633   0.01569   0.00786   0.0021   0.9068   0.8889
  -0.250  -0.0308   0.01568   0.00783   0.0009   0.9028   0.8936
   0.000   0.0000   0.01564   0.00777   0.0000   0.8991   0.8991
   0.250   0.0309   0.01568   0.00783  -0.0009   0.8936   0.9028
   0.500   0.0634   0.01569   0.00786  -0.0021   0.8888   0.9068
   0.750   0.0960   0.01567   0.00787  -0.0032   0.8848   0.9114
   1.000   0.1236   0.01571   0.00796  -0.0035   0.8777   0.9158
   1.250   0.1597   0.01570   0.00801  -0.0052   0.8724   0.9188
   1.500   0.1891   0.01571   0.00810  -0.0056   0.8644   0.9233
   1.750   0.2199   0.01562   0.00808  -0.0060   0.8562   0.9277
   2.000   0.2535   0.01551   0.00805  -0.0068   0.8432   0.9304
   2.250   0.2861   0.01527   0.00791  -0.0070   0.8262   0.9334
   2.500   0.3124   0.01499   0.00769  -0.0059   0.8027   0.9379
   2.750   0.3381   0.01471   0.00747  -0.0047   0.7786   0.9428
   3.000   0.3692   0.01445   0.00730  -0.0048   0.7511   0.9462
   3.250   0.3982   0.01426   0.00724  -0.0046   0.7181   0.9505
   3.500   0.4232   0.01406   0.00708  -0.0035   0.6675   0.9562
   3.750   0.4509   0.01412   0.00655  -0.0023   0.5124   0.9594
   4.000   0.4692   0.01530   0.00681  -0.0009   0.3275   0.9652
   4.250   0.4907   0.01643   0.00732  -0.0006   0.2058   0.9712
   4.500   0.5176   0.01733   0.00789  -0.0013   0.1423   0.9765
   4.750   0.5448   0.01811   0.00851  -0.0018   0.1100   0.9825
   5.000   0.5730   0.01891   0.00925  -0.0025   0.0918   0.9885
   5.250   0.6018   0.01971   0.01010  -0.0034   0.0770   0.9946
   5.500   0.6249   0.02055   0.01095  -0.0032   0.0670   1.0000
   5.750   0.6356   0.02125   0.01175  -0.0003   0.0611   1.0000
   6.000   0.6469   0.02187   0.01237   0.0023   0.0550   1.0000
   6.250   0.6595   0.02280   0.01336   0.0048   0.0503   1.0000
   6.500   0.6750   0.02369   0.01433   0.0068   0.0452   1.0000
   6.750   0.6900   0.02478   0.01535   0.0086   0.0408   1.0000
   7.000   0.7092   0.02607   0.01691   0.0102   0.0376   1.0000
   7.250   0.7282   0.02750   0.01852   0.0116   0.0349   1.0000
   7.500   0.7451   0.02852   0.01956   0.0129   0.0317   1.0000
   7.750   0.7627   0.03039   0.02163   0.0143   0.0295   1.0000
   8.000   0.7800   0.03262   0.02425   0.0159   0.0279   1.0000
   8.250   0.7944   0.03515   0.02718   0.0177   0.0267   1.0000
   8.500   0.8054   0.03791   0.03035   0.0198   0.0258   1.0000
   8.750   0.8133   0.04084   0.03371   0.0219   0.0253   1.0000
   9.000   0.8177   0.04390   0.03713   0.0242   0.0248   1.0000
   9.250   0.8205   0.04665   0.04017   0.0264   0.0241   1.0000
   9.500   0.8254   0.04843   0.04206   0.0280   0.0230   1.0000
   9.750   0.8227   0.05125   0.04510   0.0302   0.0226   1.0000
  10.250   0.7973   0.05766   0.05186   0.0351   0.0219   1.0000
  10.500   0.7784   0.06132   0.05574   0.0363   0.0218   1.0000
  10.750   0.7599   0.06565   0.06022   0.0361   0.0219   1.0000
  11.000   0.6787   0.08585   0.08083   0.0233   0.0258   1.0000
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