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NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il)
Reynolds number: 200,000
Max Cl/Cd: 69.47 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls413-il-200000.txt
Download as CSV file: xf-ls413-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3919   0.09506   0.09176  -0.0395   1.0000   0.0748
 -10.000  -0.4004   0.09297   0.08971  -0.0377   1.0000   0.0758
  -9.750  -0.4116   0.09040   0.08718  -0.0363   1.0000   0.0771
  -9.500  -0.4159   0.08474   0.08154  -0.0398   0.9981   0.0795
  -9.250  -0.4671   0.07030   0.06707  -0.0543   0.9940   0.0825
  -9.000  -0.5188   0.06190   0.05839  -0.0634   0.9844   0.0832
  -8.750  -0.5813   0.06917   0.06569  -0.0543   0.9934   0.0775
  -8.250  -0.5714   0.05601   0.05179  -0.0686   0.9808   0.0863
  -8.000  -0.5506   0.05346   0.04926  -0.0696   0.9767   0.0883
  -7.750  -0.5270   0.05055   0.04619  -0.0723   0.9731   0.0926
  -7.500  -0.5025   0.04618   0.04141  -0.0771   0.9702   0.1010
  -7.250  -0.4746   0.03311   0.02616  -0.0786   0.9654   0.0505
  -7.000  -0.4455   0.03028   0.02318  -0.0798   0.9622   0.0493
  -6.750  -0.4119   0.02834   0.02095  -0.0816   0.9597   0.0495
  -6.500  -0.3764   0.02676   0.01910  -0.0835   0.9578   0.0498
  -6.250  -0.3403   0.02515   0.01729  -0.0855   0.9564   0.0499
  -6.000  -0.3097   0.02399   0.01597  -0.0863   0.9536   0.0502
  -5.750  -0.2850   0.02262   0.01453  -0.0859   0.9492   0.0508
  -5.500  -0.2540   0.02136   0.01332  -0.0868   0.9466   0.0523
  -5.250  -0.2199   0.02051   0.01251  -0.0884   0.9445   0.0544
  -5.000  -0.1835   0.01985   0.01184  -0.0904   0.9428   0.0581
  -4.750  -0.1456   0.01891   0.01095  -0.0929   0.9415   0.0627
  -4.500  -0.1053   0.01820   0.01027  -0.0959   0.9403   0.0693
  -4.250  -0.0862   0.01778   0.00990  -0.0949   0.9333   0.0768
  -4.000  -0.0483   0.01708   0.00930  -0.0975   0.9308   0.1003
  -3.750   0.0018   0.01441   0.00896  -0.1047   0.9311   0.5840
  -3.500   0.0369   0.01467   0.00927  -0.1056   0.9285   0.6500
  -3.250   0.0721   0.01495   0.00950  -0.1065   0.9264   0.6807
  -3.000   0.1045   0.01529   0.00984  -0.1066   0.9246   0.7005
  -2.750   0.1159   0.01594   0.01051  -0.1029   0.9165   0.7170
  -2.500   0.1389   0.01655   0.01117  -0.1005   0.9129   0.7384
  -2.250   0.1636   0.01705   0.01169  -0.0984   0.9102   0.7574
  -2.000   0.1824   0.01744   0.01208  -0.0960   0.9049   0.7679
  -1.750   0.2093   0.01755   0.01214  -0.0959   0.8997   0.7755
  -1.500   0.2422   0.01748   0.01203  -0.0969   0.8967   0.7807
  -1.250   0.2734   0.01745   0.01198  -0.0972   0.8943   0.7859
  -1.000   0.3100   0.01740   0.01187  -0.0989   0.8925   0.7947
  -0.750   0.3203   0.01780   0.01232  -0.0954   0.8837   0.8002
  -0.500   0.3529   0.01773   0.01223  -0.0962   0.8805   0.8061
  -0.250   0.3902   0.01750   0.01196  -0.0980   0.8778   0.8112
   0.000   0.4108   0.01754   0.01203  -0.0962   0.8703   0.8160
   0.250   0.4429   0.01725   0.01173  -0.0966   0.8646   0.8216
   0.500   0.4819   0.01678   0.01124  -0.0983   0.8608   0.8266
   0.750   0.5029   0.01674   0.01122  -0.0966   0.8518   0.8305
   1.000   0.5373   0.01612   0.01059  -0.0969   0.8456   0.8344
   1.250   0.5662   0.01582   0.01030  -0.0967   0.8353   0.8386
   1.500   0.6025   0.01529   0.00974  -0.0977   0.8287   0.8422
   1.750   0.6264   0.01507   0.00955  -0.0965   0.8177   0.8452
   2.000   0.6556   0.01466   0.00914  -0.0960   0.8083   0.8488
   2.250   0.6849   0.01437   0.00886  -0.0959   0.7977   0.8525
   2.500   0.7151   0.01418   0.00870  -0.0963   0.7862   0.8563
   2.750   0.7427   0.01390   0.00844  -0.0957   0.7752   0.8596
   3.000   0.7703   0.01361   0.00815  -0.0951   0.7631   0.8631
   3.250   0.7975   0.01341   0.00799  -0.0947   0.7475   0.8669
   3.500   0.8256   0.01326   0.00786  -0.0945   0.7284   0.8710
   3.750   0.8506   0.01310   0.00773  -0.0936   0.7050   0.8748
   4.000   0.8747   0.01295   0.00757  -0.0924   0.6748   0.8787
   4.250   0.8990   0.01294   0.00743  -0.0914   0.6266   0.8828
   4.500   0.9197   0.01335   0.00737  -0.0898   0.5341   0.8875
   4.750   0.9274   0.01429   0.00770  -0.0859   0.4290   0.8921
   5.000   0.9371   0.01539   0.00829  -0.0830   0.3389   0.8972
   5.250   0.9510   0.01650   0.00896  -0.0811   0.2704   0.9023
   5.500   0.9636   0.01727   0.00949  -0.0786   0.2285   0.9074
   5.750   0.9790   0.01806   0.01007  -0.0767   0.2004   0.9137
   6.000   0.9963   0.01871   0.01064  -0.0752   0.1808   0.9198
   6.250   1.0123   0.01938   0.01122  -0.0733   0.1670   0.9265
   6.500   1.0298   0.02006   0.01183  -0.0718   0.1558   0.9336
   6.750   1.0477   0.02055   0.01238  -0.0702   0.1465   0.9421
   7.000   1.0627   0.02127   0.01301  -0.0683   0.1387   0.9523
   7.250   1.0801   0.02160   0.01345  -0.0666   0.1320   0.9678
   7.500   1.0994   0.02236   0.01413  -0.0657   0.1253   1.0000
   7.750   1.1257   0.02311   0.01497  -0.0662   0.1189   1.0000
   8.000   1.1505   0.02396   0.01579  -0.0665   0.1131   1.0000
   8.250   1.1765   0.02500   0.01684  -0.0669   0.1076   1.0000
   8.500   1.2007   0.02579   0.01769  -0.0670   0.1023   1.0000
   8.750   1.2284   0.02715   0.01892  -0.0678   0.0969   1.0000
   9.000   1.2498   0.02788   0.01983  -0.0673   0.0930   1.0000
   9.250   1.2713   0.02874   0.02074  -0.0670   0.0887   1.0000
   9.500   1.3001   0.03033   0.02220  -0.0679   0.0839   1.0000
   9.750   1.3173   0.03111   0.02320  -0.0667   0.0810   1.0000
  10.000   1.3361   0.03209   0.02430  -0.0659   0.0776   1.0000
  10.250   1.3550   0.03309   0.02528  -0.0652   0.0746   1.0000
  10.500   1.3795   0.03485   0.02708  -0.0653   0.0712   1.0000
  10.750   1.3931   0.03594   0.02837  -0.0637   0.0688   1.0000
  11.000   1.4079   0.03716   0.02973  -0.0623   0.0663   1.0000
  11.250   1.4233   0.03836   0.03098  -0.0612   0.0642   1.0000
  11.500   1.4455   0.04019   0.03278  -0.0611   0.0619   1.0000
  11.750   1.4562   0.04218   0.03502  -0.0594   0.0603   1.0000
  12.000   1.4625   0.04382   0.03691  -0.0572   0.0588   1.0000
  12.250   1.4692   0.04555   0.03883  -0.0551   0.0572   1.0000
  12.500   1.4750   0.04730   0.04075  -0.0532   0.0558   1.0000
  12.750   1.4816   0.04906   0.04262  -0.0515   0.0547   1.0000
  13.000   1.4897   0.05091   0.04455  -0.0500   0.0536   1.0000
  13.250   1.4991   0.05351   0.04722  -0.0489   0.0525   1.0000
  13.500   1.4939   0.05729   0.05127  -0.0468   0.0517   1.0000
  13.750   1.4822   0.06039   0.05467  -0.0443   0.0514   1.0000
  14.000   1.4678   0.06400   0.05858  -0.0422   0.0510   1.0000
  14.250   1.4502   0.06815   0.06303  -0.0406   0.0507   1.0000
  14.500   1.4294   0.07287   0.06804  -0.0395   0.0504   1.0000
  14.750   1.4050   0.07829   0.07375  -0.0392   0.0502   1.0000
  15.000   1.3766   0.08460   0.08035  -0.0399   0.0501   1.0000
  15.250   1.3440   0.09207   0.08809  -0.0419   0.0502   1.0000
  15.500   1.3061   0.10130   0.09759  -0.0460   0.0503   1.0000
  15.750   1.2610   0.11331   0.10987  -0.0529   0.0508   1.0000
  16.000   1.2010   0.13080   0.12759  -0.0647   0.0515   1.0000
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