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LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LWK 79-100 (lwk79100-il)
Reynolds number: 100,000
Max Cl/Cd: 35.51 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk79100-il-100000-n5.txt
Download as CSV file: xf-lwk79100-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 79-100                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.8119   0.09724   0.09206   0.0066   1.0000   0.0298
 -12.250  -0.8396   0.08635   0.08111  -0.0010   1.0000   0.0294
 -12.000  -0.8675   0.07681   0.07145  -0.0082   1.0000   0.0292
 -11.750  -0.8917   0.06927   0.06374  -0.0137   1.0000   0.0290
 -11.500  -0.9135   0.06309   0.05738  -0.0178   1.0000   0.0288
 -11.250  -0.9334   0.05800   0.05207  -0.0204   1.0000   0.0288
 -11.000  -0.9521   0.05385   0.04765  -0.0210   1.0000   0.0290
 -10.750  -0.9661   0.05034   0.04385  -0.0198   1.0000   0.0292
 -10.500  -0.9723   0.04681   0.03991  -0.0188   1.0000   0.0296
 -10.250  -0.9706   0.04353   0.03632  -0.0178   1.0000   0.0302
 -10.000  -0.9606   0.04129   0.03397  -0.0170   1.0000   0.0312
  -9.750  -0.9482   0.03956   0.03211  -0.0163   1.0000   0.0328
  -9.500  -0.9353   0.03756   0.02985  -0.0154   1.0000   0.0347
  -9.250  -0.9206   0.03531   0.02724  -0.0145   1.0000   0.0366
  -9.000  -0.9035   0.03318   0.02472  -0.0135   1.0000   0.0381
  -8.750  -0.8859   0.03133   0.02284  -0.0128   1.0000   0.0404
  -8.500  -0.8664   0.03002   0.02143  -0.0122   1.0000   0.0431
  -8.250  -0.8459   0.02852   0.01972  -0.0114   1.0000   0.0459
  -8.000  -0.8247   0.02707   0.01805  -0.0105   1.0000   0.0486
  -7.750  -0.8046   0.02577   0.01679  -0.0099   1.0000   0.0522
  -7.500  -0.7830   0.02465   0.01554  -0.0091   1.0000   0.0562
  -7.250  -0.7611   0.02351   0.01426  -0.0083   1.0000   0.0600
  -7.000  -0.7402   0.02244   0.01322  -0.0075   1.0000   0.0654
  -6.750  -0.7176   0.02154   0.01218  -0.0068   1.0000   0.0718
  -6.500  -0.6964   0.02050   0.01121  -0.0060   1.0000   0.0788
  -6.250  -0.6741   0.01962   0.01032  -0.0053   1.0000   0.0893
  -6.000  -0.6515   0.01877   0.00950  -0.0046   1.0000   0.1034
  -5.750  -0.6286   0.01797   0.00875  -0.0040   1.0000   0.1224
  -5.500  -0.6058   0.01720   0.00810  -0.0034   1.0000   0.1484
  -5.250  -0.5826   0.01649   0.00749  -0.0029   1.0000   0.1803
  -5.000  -0.5595   0.01579   0.00696  -0.0023   1.0000   0.2181
  -4.750  -0.5366   0.01511   0.00649  -0.0017   1.0000   0.2638
  -4.500  -0.5137   0.01449   0.00613  -0.0010   1.0000   0.3168
  -4.250  -0.4905   0.01399   0.00583  -0.0003   1.0000   0.3707
  -4.000  -0.4670   0.01361   0.00564   0.0006   1.0000   0.4192
  -3.750  -0.4432   0.01334   0.00551   0.0014   1.0000   0.4614
  -3.500  -0.4192   0.01316   0.00542   0.0023   1.0000   0.4964
  -3.250  -0.3950   0.01302   0.00532   0.0032   1.0000   0.5261
  -3.000  -0.3709   0.01291   0.00524   0.0040   1.0000   0.5519
  -2.750  -0.3475   0.01282   0.00519   0.0049   1.0000   0.5737
  -2.500  -0.3107   0.01277   0.00511   0.0030   0.9721   0.5970
  -2.250  -0.2708   0.01275   0.00508   0.0007   0.9343   0.6175
  -2.000  -0.2313   0.01273   0.00500  -0.0014   0.9004   0.6365
  -1.750  -0.1954   0.01272   0.00490  -0.0026   0.8709   0.6537
  -1.500  -0.1641   0.01273   0.00482  -0.0029   0.8460   0.6698
  -1.250  -0.1356   0.01274   0.00476  -0.0025   0.8247   0.6853
  -1.000  -0.1084   0.01275   0.00471  -0.0020   0.8068   0.7001
  -0.750  -0.0814   0.01275   0.00468  -0.0014   0.7909   0.7134
  -0.500  -0.0543   0.01274   0.00465  -0.0009   0.7765   0.7256
  -0.250  -0.0271   0.01273   0.00463  -0.0004   0.7629   0.7377
   0.000   0.0000   0.01273   0.00462   0.0000   0.7500   0.7500
   0.250   0.0271   0.01273   0.00462   0.0004   0.7377   0.7629
   0.500   0.0543   0.01274   0.00465   0.0009   0.7256   0.7765
   0.750   0.0814   0.01275   0.00468   0.0014   0.7134   0.7909
   1.000   0.1084   0.01275   0.00471   0.0020   0.7001   0.8068
   1.250   0.1356   0.01274   0.00476   0.0025   0.6853   0.8248
   1.500   0.1641   0.01273   0.00482   0.0029   0.6698   0.8460
   1.750   0.1954   0.01272   0.00490   0.0026   0.6538   0.8709
   2.000   0.2313   0.01273   0.00500   0.0014   0.6365   0.9004
   2.250   0.2708   0.01275   0.00508  -0.0007   0.6175   0.9344
   2.500   0.3107   0.01277   0.00511  -0.0030   0.5971   0.9722
   2.750   0.3474   0.01282   0.00519  -0.0049   0.5737   1.0000
   3.000   0.3708   0.01291   0.00524  -0.0040   0.5519   1.0000
   3.250   0.3949   0.01302   0.00532  -0.0032   0.5260   1.0000
   3.500   0.4191   0.01316   0.00542  -0.0023   0.4963   1.0000
   3.750   0.4431   0.01334   0.00550  -0.0014   0.4613   1.0000
   4.000   0.4670   0.01361   0.00564  -0.0006   0.4192   1.0000
   4.250   0.4905   0.01399   0.00583   0.0003   0.3708   1.0000
   4.500   0.5136   0.01449   0.00613   0.0010   0.3167   1.0000
   4.750   0.5365   0.01511   0.00649   0.0017   0.2638   1.0000
   5.000   0.5595   0.01579   0.00696   0.0023   0.2181   1.0000
   5.250   0.5826   0.01649   0.00749   0.0029   0.1804   1.0000
   5.500   0.6058   0.01720   0.00810   0.0034   0.1484   1.0000
   5.750   0.6287   0.01797   0.00875   0.0040   0.1224   1.0000
   6.000   0.6515   0.01877   0.00950   0.0046   0.1033   1.0000
   6.250   0.6741   0.01962   0.01032   0.0053   0.0893   1.0000
   6.500   0.6964   0.02050   0.01121   0.0060   0.0788   1.0000
   6.750   0.7177   0.02154   0.01219   0.0068   0.0717   1.0000
   7.000   0.7403   0.02244   0.01322   0.0075   0.0653   1.0000
   7.250   0.7612   0.02352   0.01426   0.0082   0.0600   1.0000
   7.500   0.7832   0.02465   0.01554   0.0091   0.0562   1.0000
   7.750   0.8048   0.02577   0.01679   0.0098   0.0521   1.0000
   8.000   0.8248   0.02708   0.01806   0.0105   0.0486   1.0000
   8.250   0.8461   0.02852   0.01973   0.0113   0.0459   1.0000
   8.500   0.8666   0.03003   0.02144   0.0121   0.0431   1.0000
   8.750   0.8861   0.03134   0.02284   0.0128   0.0403   1.0000
   9.000   0.9038   0.03319   0.02473   0.0135   0.0381   1.0000
   9.250   0.9208   0.03533   0.02727   0.0144   0.0366   1.0000
   9.500   0.9355   0.03757   0.02987   0.0153   0.0347   1.0000
   9.750   0.9485   0.03960   0.03216   0.0162   0.0328   1.0000
  10.000   0.9609   0.04133   0.03402   0.0170   0.0313   1.0000
  10.250   0.9709   0.04355   0.03634   0.0177   0.0302   1.0000
  10.500   0.9729   0.04682   0.03991   0.0187   0.0296   1.0000
  10.750   0.9663   0.05040   0.04391   0.0197   0.0292   1.0000
  11.000   0.9525   0.05387   0.04768   0.0209   0.0290   1.0000
  11.250   0.9343   0.05801   0.05207   0.0203   0.0289   1.0000
  11.500   0.9145   0.06309   0.05737   0.0177   0.0289   1.0000
  11.750   0.8913   0.06948   0.06396   0.0134   0.0289   1.0000
  12.000   0.8682   0.07687   0.07151   0.0080   0.0292   1.0000
  12.250   0.8400   0.08650   0.08126   0.0007   0.0294   1.0000
  12.500   0.8136   0.09706   0.09188  -0.0066   0.0298   1.0000
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