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LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-080 (lwk80080-il)
Reynolds number: 200,000
Max Cl/Cd: 45.92 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80080-il-200000.txt
Download as CSV file: xf-lwk80080-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-080                                      
  
 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  -0.4813   0.11992   0.11657  -0.0008   1.0000   0.0426
 -11.750  -0.4903   0.11680   0.11346  -0.0035   1.0000   0.0437
 -11.500  -0.4979   0.11317   0.10985  -0.0063   1.0000   0.0442
 -11.250  -0.5038   0.10908   0.10577  -0.0088   1.0000   0.0444
 -11.000  -0.5087   0.10471   0.10142  -0.0111   1.0000   0.0446
 -10.750  -0.5138   0.10001   0.09673  -0.0135   1.0000   0.0447
 -10.500  -0.5198   0.09502   0.09175  -0.0161   1.0000   0.0447
 -10.250  -0.5108   0.08993   0.08669  -0.0122   1.0000   0.0469
 -10.000  -0.5097   0.08608   0.08284  -0.0126   1.0000   0.0479
  -9.750  -0.5125   0.08170   0.07848  -0.0138   1.0000   0.0488
  -9.500  -0.5173   0.07701   0.07381  -0.0152   1.0000   0.0504
  -9.250  -0.5262   0.07161   0.06844  -0.0175   1.0000   0.0509
  -9.000  -0.5387   0.06574   0.06260  -0.0207   1.0000   0.0513
  -8.750  -0.5602   0.05899   0.05585  -0.0257   1.0000   0.0508
  -8.500  -0.5842   0.05375   0.05057  -0.0281   1.0000   0.0505
  -8.250  -0.7064   0.06402   0.06025  -0.0236   1.0000   0.0464
  -8.000  -0.7010   0.06064   0.05685  -0.0229   1.0000   0.0475
  -7.750  -0.6966   0.05735   0.05348  -0.0220   1.0000   0.0491
  -7.500  -0.6919   0.05401   0.05000  -0.0210   1.0000   0.0510
  -7.250  -0.6868   0.05055   0.04629  -0.0197   1.0000   0.0539
  -7.000  -0.6896   0.04625   0.04141  -0.0170   1.0000   0.0592
  -6.750  -0.6763   0.04287   0.03807  -0.0160   1.0000   0.0615
  -6.500  -0.6659   0.03330   0.02736  -0.0105   1.0000   0.0311
  -6.250  -0.6537   0.02946   0.02311  -0.0081   1.0000   0.0301
  -6.000  -0.6366   0.02814   0.02131  -0.0058   1.0000   0.0330
  -5.750  -0.6171   0.02607   0.01892  -0.0040   1.0000   0.0324
  -5.500  -0.5986   0.02294   0.01545  -0.0021   1.0000   0.0321
  -5.250  -0.5785   0.02094   0.01320  -0.0004   1.0000   0.0323
  -5.000  -0.5591   0.01871   0.01078   0.0014   1.0000   0.0332
  -4.750  -0.5436   0.01695   0.00904   0.0037   1.0000   0.0377
  -4.500  -0.5292   0.01609   0.00812   0.0062   1.0000   0.0416
  -4.250  -0.5168   0.01519   0.00718   0.0090   1.0000   0.0469
  -4.000  -0.5030   0.01460   0.00657   0.0115   1.0000   0.0589
  -3.750  -0.4898   0.01388   0.00591   0.0139   1.0000   0.0735
  -3.500  -0.4756   0.01320   0.00525   0.0162   1.0000   0.0937
  -3.250  -0.4629   0.01234   0.00471   0.0187   1.0000   0.1495
  -3.000  -0.4576   0.01043   0.00425   0.0218   0.9984   0.4381
  -2.750  -0.4409   0.00960   0.00462   0.0245   0.9927   0.7230
  -2.500  -0.4125   0.00977   0.00485   0.0250   0.9882   0.7919
  -2.250  -0.3836   0.00993   0.00499   0.0254   0.9835   0.8318
  -2.000  -0.3521   0.01007   0.00507   0.0252   0.9799   0.8604
  -1.750  -0.3232   0.01014   0.00510   0.0254   0.9753   0.8819
  -1.500  -0.2891   0.01025   0.00517   0.0246   0.9721   0.9038
  -1.250  -0.2490   0.01046   0.00535   0.0229   0.9706   0.9287
  -1.000  -0.1938   0.01081   0.00562   0.0180   0.9718   0.9461
  -0.750  -0.1433   0.01101   0.00574   0.0134   0.9713   0.9555
  -0.500  -0.0911   0.01111   0.00581   0.0081   0.9708   0.9586
  -0.250  -0.0427   0.01116   0.00582   0.0035   0.9693   0.9617
   0.000  -0.0001   0.01118   0.00582   0.0000   0.9660   0.9660
   0.250   0.0425   0.01116   0.00581  -0.0035   0.9617   0.9693
   0.500   0.0912   0.01111   0.00580  -0.0081   0.9586   0.9708
   0.750   0.1445   0.01100   0.00574  -0.0136   0.9553   0.9711
   1.000   0.1941   0.01081   0.00561  -0.0181   0.9460   0.9718
   1.250   0.2506   0.01043   0.00532  -0.0231   0.9274   0.9702
   1.500   0.2892   0.01023   0.00514  -0.0245   0.9018   0.9718
   1.750   0.3233   0.01014   0.00511  -0.0254   0.8823   0.9753
   2.000   0.3521   0.01008   0.00509  -0.0252   0.8612   0.9800
   2.250   0.3837   0.00994   0.00502  -0.0255   0.8338   0.9835
   2.500   0.4120   0.00976   0.00481  -0.0248   0.7887   0.9882
   2.750   0.4408   0.00960   0.00461  -0.0245   0.7221   0.9927
   3.000   0.4577   0.01045   0.00425  -0.0219   0.4347   0.9985
   3.250   0.4632   0.01230   0.00470  -0.0187   0.1535   1.0000
   3.500   0.4755   0.01322   0.00527  -0.0162   0.0952   1.0000
   3.750   0.4890   0.01398   0.00597  -0.0138   0.0713   1.0000
   4.000   0.5035   0.01452   0.00651  -0.0116   0.0545   1.0000
   4.250   0.5149   0.01550   0.00743  -0.0088   0.0446   1.0000
   4.500   0.5293   0.01606   0.00811  -0.0062   0.0393   1.0000
   4.750   0.5429   0.01699   0.00902  -0.0036   0.0349   1.0000
   5.000   0.5589   0.01940   0.01150  -0.0013   0.0325   1.0000
   5.250   0.5785   0.02089   0.01317   0.0005   0.0320   1.0000
   5.500   0.5986   0.02283   0.01537   0.0023   0.0316   1.0000
   5.750   0.6171   0.02599   0.01886   0.0041   0.0323   1.0000
   6.000   0.6362   0.02842   0.02162   0.0059   0.0330   1.0000
   6.500   0.6683   0.03428   0.02861   0.0116   0.0366   1.0000
  14.500   0.6834   0.17819   0.17440  -0.0332   0.0255   1.0000
  14.750   0.6896   0.18190   0.17811  -0.0345   0.0243   1.0000
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