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LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LWK 79-100 (lwk79100-il)
Reynolds number: 50,000
Max Cl/Cd: 27.1 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk79100-il-50000-n5.txt
Download as CSV file: xf-lwk79100-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7553   0.09698   0.08980   0.0030   1.0000   0.0588
 -11.000  -0.7754   0.08810   0.08092  -0.0031   1.0000   0.0584
 -10.750  -0.7985   0.07998   0.07276  -0.0089   1.0000   0.0578
 -10.500  -0.8220   0.07314   0.06584  -0.0136   1.0000   0.0573
 -10.250  -0.8459   0.06757   0.06013  -0.0164   1.0000   0.0571
 -10.000  -0.8653   0.06295   0.05530  -0.0170   1.0000   0.0571
  -9.750  -0.8780   0.05833   0.05033  -0.0172   1.0000   0.0576
  -9.500  -0.8842   0.05387   0.04541  -0.0169   1.0000   0.0585
  -9.250  -0.8834   0.04972   0.04068  -0.0163   1.0000   0.0595
  -9.000  -0.8700   0.04710   0.03806  -0.0158   1.0000   0.0620
  -8.750  -0.8566   0.04476   0.03553  -0.0152   1.0000   0.0656
  -8.500  -0.8428   0.04187   0.03220  -0.0145   1.0000   0.0690
  -8.250  -0.8259   0.03894   0.02873  -0.0137   1.0000   0.0719
  -8.000  -0.8063   0.03708   0.02693  -0.0131   1.0000   0.0765
  -7.750  -0.7861   0.03514   0.02465  -0.0124   1.0000   0.0825
  -7.500  -0.7643   0.03320   0.02260  -0.0116   1.0000   0.0875
  -7.250  -0.7427   0.03164   0.02090  -0.0108   1.0000   0.0951
  -7.000  -0.7214   0.03015   0.01939  -0.0100   1.0000   0.1040
  -6.750  -0.6995   0.02867   0.01780  -0.0091   1.0000   0.1141
  -6.500  -0.6787   0.02735   0.01645  -0.0083   1.0000   0.1283
  -6.250  -0.6583   0.02603   0.01519  -0.0074   1.0000   0.1458
  -6.000  -0.6378   0.02475   0.01398  -0.0066   1.0000   0.1701
  -5.750  -0.6177   0.02351   0.01290  -0.0058   1.0000   0.2014
  -5.500  -0.5973   0.02236   0.01193  -0.0051   1.0000   0.2421
  -5.250  -0.5770   0.02132   0.01116  -0.0042   1.0000   0.2912
  -5.000  -0.5561   0.02052   0.01063  -0.0032   1.0000   0.3473
  -4.750  -0.5347   0.01997   0.01028  -0.0019   1.0000   0.4034
  -4.500  -0.5129   0.01964   0.01012  -0.0004   1.0000   0.4530
  -4.250  -0.4907   0.01945   0.00997   0.0011   1.0000   0.4963
  -4.000  -0.4682   0.01932   0.00982   0.0026   1.0000   0.5338
  -3.750  -0.4457   0.01919   0.00965   0.0040   1.0000   0.5661
  -3.500  -0.4232   0.01905   0.00947   0.0055   1.0000   0.5945
  -3.250  -0.4007   0.01889   0.00929   0.0070   1.0000   0.6194
  -3.000  -0.3784   0.01869   0.00906   0.0084   1.0000   0.6433
  -2.750  -0.3563   0.01848   0.00885   0.0098   1.0000   0.6652
  -2.500  -0.3347   0.01825   0.00858   0.0112   1.0000   0.6868
  -2.250  -0.3136   0.01802   0.00839   0.0127   1.0000   0.7066
  -2.000  -0.2938   0.01779   0.00819   0.0141   1.0000   0.7270
  -1.750  -0.2753   0.01757   0.00803   0.0157   1.0000   0.7469
  -1.500  -0.2585   0.01740   0.00791   0.0174   1.0000   0.7662
  -1.250  -0.2213   0.01733   0.00783   0.0153   0.9779   0.7870
  -1.000  -0.1781   0.01727   0.00778   0.0122   0.9560   0.8064
  -0.750  -0.1349   0.01722   0.00772   0.0093   0.9352   0.8245
  -0.500  -0.0907   0.01717   0.00768   0.0063   0.9156   0.8426
  -0.250  -0.0454   0.01715   0.00766   0.0031   0.8972   0.8609
   0.000   0.0000   0.01714   0.00764   0.0000   0.8794   0.8793
   0.250   0.0454   0.01715   0.00766  -0.0031   0.8609   0.8973
   0.500   0.0907   0.01717   0.00768  -0.0063   0.8427   0.9156
   0.750   0.1349   0.01721   0.00772  -0.0093   0.8245   0.9352
   1.000   0.1781   0.01727   0.00777  -0.0122   0.8064   0.9560
   1.250   0.2214   0.01733   0.00783  -0.0153   0.7870   0.9779
   1.500   0.2584   0.01740   0.00791  -0.0174   0.7662   1.0000
   1.750   0.2752   0.01757   0.00803  -0.0157   0.7469   1.0000
   2.000   0.2937   0.01779   0.00819  -0.0141   0.7270   1.0000
   2.250   0.3136   0.01802   0.00839  -0.0127   0.7066   1.0000
   2.500   0.3346   0.01825   0.00858  -0.0111   0.6868   1.0000
   2.750   0.3562   0.01848   0.00885  -0.0098   0.6653   1.0000
   3.000   0.3784   0.01869   0.00906  -0.0084   0.6433   1.0000
   3.250   0.4007   0.01889   0.00929  -0.0070   0.6194   1.0000
   3.500   0.4232   0.01905   0.00945  -0.0055   0.5945   1.0000
   3.750   0.4457   0.01919   0.00965  -0.0040   0.5661   1.0000
   4.000   0.4682   0.01932   0.00981  -0.0026   0.5338   1.0000
   4.250   0.4906   0.01945   0.00997  -0.0011   0.4963   1.0000
   4.500   0.5129   0.01964   0.01012   0.0004   0.4529   1.0000
   4.750   0.5347   0.01997   0.01028   0.0019   0.4035   1.0000
   5.000   0.5561   0.02052   0.01062   0.0032   0.3474   1.0000
   5.250   0.5771   0.02132   0.01116   0.0042   0.2911   1.0000
   5.500   0.5973   0.02236   0.01193   0.0051   0.2421   1.0000
   5.750   0.6178   0.02351   0.01290   0.0058   0.2013   1.0000
   6.000   0.6378   0.02476   0.01398   0.0066   0.1700   1.0000
   6.250   0.6583   0.02603   0.01519   0.0074   0.1456   1.0000
   6.500   0.6788   0.02735   0.01645   0.0083   0.1283   1.0000
   6.750   0.6996   0.02868   0.01781   0.0091   0.1140   1.0000
   7.000   0.7215   0.03015   0.01939   0.0100   0.1039   1.0000
   7.250   0.7428   0.03165   0.02091   0.0108   0.0951   1.0000
   7.500   0.7645   0.03321   0.02261   0.0116   0.0875   1.0000
   7.750   0.7863   0.03515   0.02466   0.0123   0.0825   1.0000
   8.000   0.8065   0.03709   0.02694   0.0131   0.0765   1.0000
   8.250   0.8261   0.03895   0.02874   0.0136   0.0719   1.0000
   8.500   0.8430   0.04188   0.03221   0.0145   0.0690   1.0000
   8.750   0.8568   0.04475   0.03552   0.0152   0.0655   1.0000
   9.000   0.8704   0.04708   0.03803   0.0158   0.0620   1.0000
   9.250   0.8835   0.04975   0.04073   0.0163   0.0595   1.0000
   9.500   0.8844   0.05390   0.04544   0.0169   0.0585   1.0000
   9.750   0.8784   0.05836   0.05035   0.0171   0.0576   1.0000
  10.000   0.8660   0.06296   0.05530   0.0169   0.0572   1.0000
  10.250   0.8461   0.06763   0.06019   0.0163   0.0571   1.0000
  10.500   0.8232   0.07312   0.06582   0.0136   0.0574   1.0000
  10.750   0.7983   0.08015   0.07294   0.0086   0.0578   1.0000
  11.000   0.7764   0.08810   0.08092   0.0030   0.0584   1.0000
  11.250   0.7564   0.09695   0.08977  -0.0030   0.0588   1.0000
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