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LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-120/K25 (lwk80120k25-il)
Reynolds number: 50,000
Max Cl/Cd: 27.19 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80120k25-il-50000-n5.txt
Download as CSV file: xf-lwk80120k25-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-120/K25                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6676   0.09988   0.09246  -0.0295   1.0000   0.0568
 -12.000  -0.6876   0.09173   0.08430  -0.0346   1.0000   0.0564
 -11.750  -0.7102   0.08451   0.07705  -0.0387   1.0000   0.0559
 -11.500  -0.7344   0.07829   0.07077  -0.0415   1.0000   0.0554
 -11.250  -0.7593   0.07296   0.06532  -0.0428   1.0000   0.0552
 -11.000  -0.7813   0.06848   0.06069  -0.0428   1.0000   0.0549
 -10.750  -0.8046   0.06462   0.05661  -0.0413   1.0000   0.0555
 -10.500  -0.8225   0.06127   0.05305  -0.0387   1.0000   0.0558
 -10.250  -0.8382   0.05798   0.04943  -0.0358   1.0000   0.0566
 -10.000  -0.8481   0.05468   0.04571  -0.0329   1.0000   0.0574
  -9.750  -0.8482   0.05156   0.04232  -0.0306   1.0000   0.0587
  -9.500  -0.8400   0.04899   0.03958  -0.0291   1.0000   0.0603
  -9.250  -0.8313   0.04678   0.03720  -0.0273   1.0000   0.0628
  -9.000  -0.8226   0.04455   0.03466  -0.0254   1.0000   0.0662
  -8.750  -0.8135   0.04209   0.03168  -0.0231   1.0000   0.0697
  -8.500  -0.7961   0.03984   0.02934  -0.0220   1.0000   0.0729
  -8.250  -0.7804   0.03823   0.02762  -0.0206   1.0000   0.0777
  -8.000  -0.7633   0.03650   0.02542  -0.0190   1.0000   0.0835
  -7.750  -0.7418   0.03484   0.02387  -0.0183   1.0000   0.0889
  -7.500  -0.7223   0.03353   0.02227  -0.0169   1.0000   0.0969
  -7.250  -0.7015   0.03224   0.02109  -0.0160   1.0000   0.1046
  -7.000  -0.6800   0.03110   0.01985  -0.0148   1.0000   0.1143
  -6.750  -0.6619   0.03017   0.01881  -0.0132   1.0000   0.1257
  -6.500  -0.6475   0.02923   0.01792  -0.0111   1.0000   0.1365
  -6.250  -0.6378   0.02842   0.01715  -0.0084   1.0000   0.1495
  -6.000  -0.6303   0.02762   0.01640  -0.0053   1.0000   0.1640
  -5.750  -0.6243   0.02682   0.01566  -0.0019   1.0000   0.1816
  -5.500  -0.6201   0.02595   0.01496   0.0016   1.0000   0.2054
  -5.250  -0.6170   0.02500   0.01424   0.0052   1.0000   0.2387
  -5.000  -0.6154   0.02392   0.01350   0.0090   1.0000   0.2919
  -4.750  -0.6155   0.02271   0.01291   0.0133   1.0000   0.3790
  -4.500  -0.6051   0.02227   0.01363   0.0181   1.0000   0.5426
  -4.250  -0.5874   0.02303   0.01458   0.0221   1.0000   0.6476
  -4.000  -0.5812   0.02330   0.01471   0.0266   1.0000   0.6984
  -3.750  -0.5669   0.02380   0.01504   0.0301   0.9988   0.7365
  -3.500  -0.5409   0.02451   0.01553   0.0317   0.9942   0.7714
  -3.250  -0.5105   0.02531   0.01614   0.0328   0.9906   0.8019
  -3.000  -0.4721   0.02620   0.01680   0.0327   0.9885   0.8308
  -2.750  -0.4316   0.02681   0.01721   0.0316   0.9863   0.8550
  -2.500  -0.3845   0.02721   0.01739   0.0286   0.9846   0.8722
  -2.250  -0.3430   0.02733   0.01728   0.0259   0.9819   0.8853
  -2.000  -0.3066   0.02732   0.01711   0.0237   0.9785   0.8968
  -1.750  -0.2587   0.02730   0.01693   0.0193   0.9760   0.9036
  -1.500  -0.2260   0.02722   0.01671   0.0174   0.9717   0.9127
  -1.250  -0.1790   0.02718   0.01656   0.0129   0.9691   0.9179
  -1.000  -0.1487   0.02709   0.01638   0.0114   0.9642   0.9255
  -0.750  -0.1090   0.02703   0.01626   0.0081   0.9602   0.9307
  -0.500  -0.0683   0.02700   0.01619   0.0046   0.9567   0.9359
  -0.250  -0.0403   0.02697   0.01612   0.0035   0.9510   0.9425
   0.000   0.0001   0.02695   0.01609   0.0000   0.9465   0.9465
   0.250   0.0406   0.02697   0.01612  -0.0035   0.9424   0.9510
   0.500   0.0682   0.02700   0.01618  -0.0045   0.9359   0.9567
   0.750   0.1088   0.02703   0.01626  -0.0081   0.9308   0.9602
   1.000   0.1487   0.02709   0.01638  -0.0114   0.9256   0.9642
   1.250   0.1790   0.02718   0.01656  -0.0129   0.9179   0.9691
   1.750   0.2586   0.02730   0.01693  -0.0193   0.9036   0.9760
   2.000   0.3069   0.02731   0.01710  -0.0237   0.8969   0.9785
   2.250   0.3436   0.02731   0.01727  -0.0260   0.8852   0.9818
   2.500   0.3848   0.02720   0.01735  -0.0287   0.8721   0.9845
   2.750   0.4312   0.02682   0.01722  -0.0315   0.8552   0.9864
   3.000   0.4722   0.02619   0.01680  -0.0327   0.8307   0.9885
   3.250   0.5106   0.02531   0.01613  -0.0328   0.8020   0.9906
   3.500   0.5411   0.02450   0.01553  -0.0317   0.7713   0.9943
   3.750   0.5669   0.02378   0.01502  -0.0300   0.7360   0.9989
   4.000   0.5809   0.02330   0.01470  -0.0266   0.6980   1.0000
   4.250   0.5873   0.02302   0.01458  -0.0221   0.6478   1.0000
   4.500   0.6052   0.02226   0.01361  -0.0181   0.5416   1.0000
   4.750   0.6155   0.02270   0.01291  -0.0133   0.3797   1.0000
   5.000   0.6153   0.02392   0.01350  -0.0090   0.2918   1.0000
   5.250   0.6170   0.02499   0.01423  -0.0052   0.2391   1.0000
   5.500   0.6200   0.02595   0.01495  -0.0016   0.2052   1.0000
   5.750   0.6242   0.02681   0.01565   0.0019   0.1815   1.0000
   6.000   0.6302   0.02762   0.01639   0.0053   0.1637   1.0000
   6.250   0.6378   0.02842   0.01714   0.0084   0.1496   1.0000
   6.500   0.6476   0.02923   0.01792   0.0112   0.1363   1.0000
   6.750   0.6618   0.03017   0.01881   0.0133   0.1255   1.0000
   7.000   0.6798   0.03110   0.01984   0.0149   0.1142   1.0000
   7.250   0.7016   0.03224   0.02109   0.0160   0.1047   1.0000
   7.500   0.7219   0.03351   0.02227   0.0170   0.0968   1.0000
   7.750   0.7414   0.03482   0.02384   0.0183   0.0888   1.0000
   8.000   0.7637   0.03652   0.02547   0.0190   0.0835   1.0000
   8.250   0.7804   0.03825   0.02763   0.0206   0.0776   1.0000
   8.500   0.7964   0.03987   0.02937   0.0220   0.0729   1.0000
   8.750   0.8133   0.04213   0.03173   0.0231   0.0696   1.0000
   9.000   0.8227   0.04457   0.03469   0.0254   0.0661   1.0000
   9.250   0.8313   0.04670   0.03709   0.0273   0.0624   1.0000
   9.500   0.8401   0.04901   0.03960   0.0291   0.0603   1.0000
   9.750   0.8484   0.05161   0.04236   0.0306   0.0586   1.0000
  10.000   0.8481   0.05475   0.04579   0.0328   0.0575   1.0000
  10.250   0.8369   0.05810   0.04957   0.0358   0.0565   1.0000
  10.500   0.8229   0.06138   0.05315   0.0387   0.0559   1.0000
  10.750   0.8029   0.06474   0.05674   0.0413   0.0553   1.0000
  11.000   0.7819   0.06858   0.06078   0.0427   0.0551   1.0000
  11.250   0.7586   0.07311   0.06547   0.0427   0.0551   1.0000
  11.500   0.7344   0.07840   0.07089   0.0413   0.0554   1.0000
  11.750   0.7134   0.08432   0.07685   0.0388   0.0561   1.0000
  12.000   0.6876   0.09196   0.08453   0.0343   0.0564   1.0000
  12.250   0.6679   0.10011   0.09268   0.0293   0.0568   1.0000
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