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LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LWK 79-100 (lwk79100-il)
Reynolds number: 200,000
Max Cl/Cd: 47.73 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk79100-il-200000.txt
Download as CSV file: xf-lwk79100-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7779   0.09684   0.09322   0.0054   1.0000   0.0379
 -11.750  -0.7991   0.08724   0.08365  -0.0001   1.0000   0.0369
 -11.500  -0.8327   0.07593   0.07227  -0.0087   1.0000   0.0358
 -11.250  -0.8653   0.06711   0.06330  -0.0157   1.0000   0.0351
 -11.000  -0.8960   0.06030   0.05631  -0.0203   1.0000   0.0345
 -10.750  -0.9247   0.05514   0.05093  -0.0217   1.0000   0.0339
 -10.500  -0.9487   0.05080   0.04630  -0.0203   1.0000   0.0335
 -10.250  -0.9625   0.04608   0.04119  -0.0191   1.0000   0.0333
 -10.000  -0.9649   0.04211   0.03683  -0.0178   1.0000   0.0335
  -9.750  -0.9598   0.03875   0.03310  -0.0165   1.0000   0.0341
  -9.500  -0.9497   0.03590   0.02988  -0.0153   1.0000   0.0352
  -9.250  -0.9358   0.03372   0.02732  -0.0142   1.0000   0.0369
  -9.000  -0.9188   0.03230   0.02550  -0.0130   1.0000   0.0382
  -8.750  -0.9038   0.02830   0.02124  -0.0121   1.0000   0.0401
  -8.500  -0.8830   0.02671   0.01957  -0.0115   1.0000   0.0420
  -8.250  -0.8612   0.02545   0.01817  -0.0107   1.0000   0.0449
  -8.000  -0.8385   0.02447   0.01694  -0.0099   1.0000   0.0477
  -7.750  -0.8174   0.02229   0.01468  -0.0091   1.0000   0.0508
  -7.500  -0.7945   0.02130   0.01367  -0.0085   1.0000   0.0546
  -7.250  -0.7706   0.02044   0.01267  -0.0078   1.0000   0.0585
  -7.000  -0.7488   0.01893   0.01116  -0.0070   1.0000   0.0625
  -6.750  -0.7254   0.01812   0.01035  -0.0063   1.0000   0.0680
  -6.500  -0.7025   0.01713   0.00931  -0.0055   1.0000   0.0737
  -6.250  -0.6797   0.01626   0.00846  -0.0047   1.0000   0.0813
  -6.000  -0.6570   0.01537   0.00762  -0.0039   1.0000   0.0921
  -5.750  -0.6340   0.01454   0.00685  -0.0032   1.0000   0.1091
  -5.500  -0.6115   0.01364   0.00612  -0.0024   1.0000   0.1373
  -5.250  -0.5888   0.01282   0.00553  -0.0018   1.0000   0.1783
  -5.000  -0.5655   0.01212   0.00504  -0.0012   1.0000   0.2252
  -4.750  -0.5425   0.01145   0.00464  -0.0006   1.0000   0.2772
  -4.500  -0.5194   0.01088   0.00434   0.0001   1.0000   0.3378
  -4.250  -0.4959   0.01043   0.00412   0.0009   1.0000   0.3956
  -4.000  -0.4720   0.01012   0.00399   0.0017   1.0000   0.4470
  -3.750  -0.4480   0.00991   0.00394   0.0026   1.0000   0.4905
  -3.500  -0.4236   0.00980   0.00392   0.0034   1.0000   0.5244
  -3.250  -0.3993   0.00974   0.00390   0.0043   1.0000   0.5524
  -3.000  -0.3757   0.00969   0.00392   0.0052   1.0000   0.5753
  -2.750  -0.3510   0.00969   0.00396   0.0055   0.9973   0.5963
  -2.500  -0.3021   0.00970   0.00399   0.0012   0.9696   0.6180
  -2.250  -0.2566   0.00971   0.00397  -0.0022   0.9375   0.6376
  -2.000  -0.2158   0.00972   0.00392  -0.0046   0.9048   0.6550
  -1.750  -0.1833   0.00975   0.00387  -0.0050   0.8757   0.6703
  -1.500  -0.1558   0.00979   0.00384  -0.0044   0.8521   0.6839
  -1.250  -0.1297   0.00983   0.00382  -0.0036   0.8334   0.6967
  -1.000  -0.1039   0.00987   0.00381  -0.0028   0.8169   0.7096
  -0.750  -0.0779   0.00990   0.00380  -0.0021   0.8024   0.7226
  -0.500  -0.0520   0.00993   0.00381  -0.0014   0.7893   0.7361
  -0.250  -0.0261   0.00994   0.00381  -0.0006   0.7762   0.7501
   0.000   0.0000   0.00994   0.00382   0.0000   0.7634   0.7634
   0.250   0.0261   0.00994   0.00381   0.0006   0.7501   0.7762
   0.500   0.0520   0.00993   0.00381   0.0014   0.7361   0.7893
   0.750   0.0779   0.00990   0.00380   0.0021   0.7226   0.8024
   1.000   0.1039   0.00987   0.00381   0.0028   0.7097   0.8169
   1.250   0.1298   0.00983   0.00382   0.0036   0.6967   0.8334
   1.500   0.1558   0.00979   0.00384   0.0044   0.6839   0.8521
   1.750   0.1833   0.00975   0.00387   0.0050   0.6703   0.8758
   2.000   0.2158   0.00972   0.00392   0.0046   0.6550   0.9048
   2.250   0.2566   0.00971   0.00397   0.0022   0.6376   0.9375
   2.500   0.3021   0.00970   0.00399  -0.0012   0.6179   0.9697
   2.750   0.3511   0.00969   0.00396  -0.0055   0.5964   0.9974
   3.000   0.3756   0.00969   0.00392  -0.0051   0.5755   1.0000
   3.250   0.3992   0.00974   0.00390  -0.0042   0.5525   1.0000
   3.500   0.4236   0.00980   0.00392  -0.0034   0.5245   1.0000
   3.750   0.4479   0.00991   0.00394  -0.0026   0.4906   1.0000
   4.000   0.4720   0.01012   0.00399  -0.0017   0.4470   1.0000
   4.250   0.4958   0.01043   0.00412  -0.0009   0.3955   1.0000
   4.500   0.5193   0.01088   0.00434  -0.0001   0.3378   1.0000
   4.750   0.5425   0.01145   0.00464   0.0006   0.2773   1.0000
   5.000   0.5655   0.01212   0.00504   0.0012   0.2252   1.0000
   5.250   0.5887   0.01282   0.00553   0.0018   0.1783   1.0000
   5.500   0.6115   0.01364   0.00612   0.0024   0.1373   1.0000
   5.750   0.6340   0.01454   0.00685   0.0032   0.1091   1.0000
   6.000   0.6570   0.01537   0.00762   0.0039   0.0921   1.0000
   6.250   0.6797   0.01626   0.00846   0.0047   0.0812   1.0000
   6.500   0.7026   0.01713   0.00931   0.0054   0.0737   1.0000
   6.750   0.7255   0.01812   0.01035   0.0063   0.0679   1.0000
   7.000   0.7488   0.01894   0.01116   0.0069   0.0624   1.0000
   7.250   0.7707   0.02045   0.01267   0.0078   0.0585   1.0000
   7.500   0.7946   0.02128   0.01365   0.0085   0.0545   1.0000
   7.750   0.8175   0.02229   0.01468   0.0091   0.0508   1.0000
   8.000   0.8386   0.02447   0.01695   0.0099   0.0477   1.0000
   8.250   0.8614   0.02543   0.01815   0.0107   0.0448   1.0000
   8.500   0.8831   0.02672   0.01958   0.0114   0.0421   1.0000
   8.750   0.9040   0.02832   0.02126   0.0121   0.0400   1.0000
   9.000   0.9189   0.03239   0.02559   0.0129   0.0383   1.0000
   9.250   0.9359   0.03380   0.02741   0.0141   0.0369   1.0000
   9.500   0.9501   0.03586   0.02984   0.0153   0.0351   1.0000
   9.750   0.9600   0.03878   0.03313   0.0165   0.0341   1.0000
  10.000   0.9648   0.04221   0.03693   0.0177   0.0336   1.0000
  10.250   0.9632   0.04605   0.04115   0.0190   0.0332   1.0000
  10.500   0.9494   0.05078   0.04628   0.0202   0.0335   1.0000
  10.750   0.9252   0.05516   0.05095   0.0216   0.0338   1.0000
  11.000   0.8966   0.06032   0.05633   0.0201   0.0344   1.0000
  11.250   0.8662   0.06709   0.06328   0.0156   0.0350   1.0000
  11.500   0.8336   0.07597   0.07231   0.0086   0.0358   1.0000
  11.750   0.7966   0.08815   0.08457  -0.0009   0.0369   1.0000
  12.000   0.7763   0.09764   0.09403  -0.0062   0.0379   1.0000
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