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LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-100 (lwk80100-il)
Reynolds number: 50,000
Max Cl/Cd: 26.16 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80100-il-50000.txt
Download as CSV file: xf-lwk80100-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5453   0.09877   0.09166   0.0099   1.0000   0.3896
  -8.750  -0.5983   0.06101   0.05472  -0.0291   1.0000   0.1591
  -8.500  -0.7268   0.07008   0.06324  -0.0244   1.0000   0.1516
  -8.250  -0.7373   0.06428   0.05715  -0.0241   1.0000   0.1382
  -8.000  -0.7400   0.05943   0.05197  -0.0228   1.0000   0.1303
  -7.750  -0.7429   0.05471   0.04685  -0.0210   1.0000   0.1252
  -7.500  -0.7487   0.05110   0.04234  -0.0177   1.0000   0.1208
  -7.250  -0.7332   0.04738   0.03870  -0.0167   1.0000   0.1256
  -7.000  -0.7237   0.04416   0.03510  -0.0144   1.0000   0.1278
  -6.750  -0.7121   0.04086   0.03134  -0.0120   1.0000   0.1286
  -6.500  -0.6983   0.03798   0.02798  -0.0096   1.0000   0.1313
  -6.250  -0.6831   0.03548   0.02524  -0.0076   1.0000   0.1397
  -6.000  -0.6652   0.03321   0.02256  -0.0055   1.0000   0.1474
  -5.750  -0.6434   0.03084   0.02009  -0.0042   1.0000   0.1578
  -5.500  -0.6230   0.02899   0.01812  -0.0026   1.0000   0.1746
  -5.250  -0.5949   0.02695   0.01600  -0.0018   1.0000   0.1938
  -5.000  -0.5702   0.02521   0.01452  -0.0008   1.0000   0.2277
  -4.750  -0.5490   0.02336   0.01299   0.0009   1.0000   0.2783
  -4.500  -0.5452   0.02099   0.01174   0.0051   1.0000   0.3790
  -4.250  -0.5468   0.02196   0.01479   0.0196   1.0000   0.7613
  -4.000  -0.2009   0.02697   0.01717  -0.0189   1.0000   0.9651
  -3.750  -0.1119   0.02484   0.01451  -0.0326   1.0000   1.0000
  -3.500  -0.0974   0.02418   0.01375  -0.0321   1.0000   1.0000
  -3.250  -0.0828   0.02360   0.01308  -0.0315   1.0000   1.0000
  -3.000  -0.0684   0.02311   0.01251  -0.0307   1.0000   1.0000
  -2.750  -0.0546   0.02268   0.01203  -0.0297   1.0000   1.0000
  -2.500  -0.0417   0.02234   0.01164  -0.0284   1.0000   1.0000
  -2.250  -0.0304   0.02206   0.01133  -0.0269   1.0000   1.0000
  -2.000  -0.0211   0.02188   0.01112  -0.0249   1.0000   1.0000
  -1.750  -0.0142   0.02177   0.01101  -0.0226   1.0000   1.0000
  -1.500  -0.0098   0.02174   0.01097  -0.0198   1.0000   1.0000
  -1.250  -0.0075   0.02176   0.01098  -0.0166   1.0000   1.0000
  -1.000  -0.0060   0.02179   0.01099  -0.0133   1.0000   1.0000
  -0.750  -0.0048   0.02182   0.01101  -0.0099   1.0000   1.0000
  -0.500  -0.0033   0.02185   0.01102  -0.0066   1.0000   1.0000
  -0.250  -0.0017   0.02186   0.01103  -0.0033   1.0000   1.0000
   0.000   0.0001   0.02186   0.01103   0.0000   1.0000   1.0000
   0.250   0.0018   0.02186   0.01103   0.0033   1.0000   1.0000
   0.500   0.0034   0.02185   0.01102   0.0066   1.0000   1.0000
   0.750   0.0049   0.02182   0.01101   0.0099   1.0000   1.0000
   1.000   0.0062   0.02179   0.01100   0.0133   1.0000   1.0000
   1.250   0.0076   0.02175   0.01097   0.0166   1.0000   1.0000
   1.500   0.0099   0.02174   0.01097   0.0198   1.0000   1.0000
   1.750   0.0143   0.02177   0.01101   0.0226   1.0000   1.0000
   2.000   0.0213   0.02187   0.01112   0.0250   1.0000   1.0000
   2.250   0.0305   0.02206   0.01132   0.0269   1.0000   1.0000
   2.500   0.0419   0.02233   0.01162   0.0285   1.0000   1.0000
   2.750   0.0548   0.02268   0.01203   0.0297   1.0000   1.0000
   3.000   0.0686   0.02310   0.01251   0.0307   1.0000   1.0000
   3.250   0.0830   0.02360   0.01308   0.0315   1.0000   1.0000
   3.500   0.0976   0.02417   0.01374   0.0321   1.0000   1.0000
   3.750   0.1123   0.02483   0.01451   0.0326   1.0000   1.0000
   4.000   0.2024   0.02697   0.01717   0.0187   0.9643   1.0000
   4.250   0.5471   0.02201   0.01484  -0.0198   0.7628   1.0000
   4.500   0.5465   0.02089   0.01173  -0.0053   0.3854   1.0000
   4.750   0.5502   0.02330   0.01302  -0.0010   0.2815   1.0000
   5.000   0.5706   0.02516   0.01448   0.0008   0.2303   1.0000
   5.250   0.5947   0.02686   0.01598   0.0019   0.1955   1.0000
   5.500   0.6229   0.02896   0.01809   0.0026   0.1748   1.0000
   5.750   0.6430   0.03080   0.02005   0.0042   0.1569   1.0000
   6.000   0.6651   0.03320   0.02256   0.0056   0.1472   1.0000
   6.250   0.6832   0.03545   0.02516   0.0076   0.1385   1.0000
   6.500   0.6977   0.03796   0.02800   0.0098   0.1303   1.0000
   6.750   0.7118   0.04093   0.03143   0.0121   0.1278   1.0000
   7.000   0.7237   0.04408   0.03499   0.0144   0.1260   1.0000
   7.250   0.7401   0.04759   0.03838   0.0155   0.1208   1.0000
   7.500   0.7445   0.05089   0.04230   0.0183   0.1199   1.0000
   7.750   0.7547   0.05519   0.04681   0.0198   0.1209   1.0000
   8.000   0.7386   0.05956   0.05212   0.0230   0.1296   1.0000
   8.250   0.7432   0.06443   0.05720   0.0240   0.1367   1.0000
   8.500   0.6326   0.05467   0.04829   0.0293   0.1430   1.0000
   8.750   0.6242   0.06000   0.05369   0.0297   0.1510   1.0000
   9.000   0.5883   0.06640   0.06013   0.0288   0.1648   1.0000
   9.250   0.5512   0.10236   0.09524  -0.0093   0.3708   1.0000
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