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NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il)
Reynolds number: 200,000
Max Cl/Cd: 52.51 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls417mod-il-200000.txt
Download as CSV file: xf-ls417mod-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6695   0.07181   0.06721  -0.0701   1.0000   0.0484
 -12.250  -0.6587   0.06941   0.06487  -0.0699   1.0000   0.0488
 -12.000  -0.7845   0.05807   0.05272  -0.0690   1.0000   0.0435
 -11.750  -0.7939   0.05560   0.05021  -0.0664   1.0000   0.0433
 -11.500  -0.8073   0.05338   0.04792  -0.0631   1.0000   0.0432
 -11.250  -0.8199   0.05114   0.04559  -0.0598   1.0000   0.0430
 -11.000  -0.8336   0.04916   0.04351  -0.0558   1.0000   0.0429
 -10.750  -0.8477   0.04728   0.04149  -0.0514   1.0000   0.0427
 -10.500  -0.8592   0.04528   0.03931  -0.0475   1.0000   0.0425
 -10.250  -0.8661   0.04311   0.03691  -0.0441   1.0000   0.0424
 -10.000  -0.8677   0.04087   0.03440  -0.0414   1.0000   0.0423
  -9.750  -0.8505   0.03812   0.03128  -0.0418   0.9980   0.0425
  -9.500  -0.8235   0.03551   0.02827  -0.0435   0.9948   0.0429
  -9.250  -0.7932   0.03338   0.02567  -0.0454   0.9922   0.0435
  -9.000  -0.7636   0.03185   0.02426  -0.0464   0.9892   0.0446
  -8.750  -0.7321   0.03073   0.02311  -0.0479   0.9857   0.0460
  -8.500  -0.6997   0.02942   0.02156  -0.0495   0.9828   0.0475
  -8.250  -0.6652   0.02806   0.02003  -0.0512   0.9805   0.0487
  -8.000  -0.6322   0.02697   0.01900  -0.0525   0.9767   0.0500
  -7.750  -0.5974   0.02596   0.01797  -0.0540   0.9718   0.0516
  -7.500  -0.5576   0.02490   0.01682  -0.0564   0.9683   0.0538
  -7.250  -0.5170   0.02396   0.01598  -0.0591   0.9658   0.0565
  -7.000  -0.4883   0.02323   0.01518  -0.0594   0.9595   0.0589
  -6.750  -0.4533   0.02226   0.01436  -0.0612   0.9554   0.0617
  -6.500  -0.4130   0.02132   0.01345  -0.0639   0.9525   0.0657
  -6.250  -0.3697   0.02038   0.01257  -0.0674   0.9504   0.0717
  -6.000  -0.3444   0.01973   0.01197  -0.0675   0.9430   0.0777
  -5.750  -0.3054   0.01866   0.01106  -0.0704   0.9392   0.0896
  -5.500  -0.2637   0.01729   0.01001  -0.0742   0.9363   0.1276
  -5.250  -0.2205   0.01545   0.00893  -0.0792   0.9339   0.2492
  -5.000  -0.1882   0.01430   0.00838  -0.0814   0.9264   0.3712
  -4.750  -0.1498   0.01340   0.00811  -0.0839   0.9211   0.4928
  -4.500  -0.1146   0.01340   0.00843  -0.0844   0.9166   0.5726
  -4.250  -0.0848   0.01362   0.00863  -0.0841   0.9087   0.6108
  -4.000  -0.0550   0.01396   0.00897  -0.0832   0.9007   0.6358
  -3.750  -0.0251   0.01441   0.00939  -0.0821   0.8937   0.6560
  -3.500   0.0010   0.01482   0.00973  -0.0807   0.8832   0.6729
  -3.250   0.0248   0.01532   0.01024  -0.0779   0.8757   0.6799
  -3.000   0.0501   0.01562   0.01049  -0.0765   0.8650   0.6916
  -2.750   0.0753   0.01585   0.01068  -0.0746   0.8558   0.6984
  -2.500   0.0964   0.01624   0.01107  -0.0717   0.8447   0.7049
  -2.250   0.1257   0.01635   0.01106  -0.0712   0.8332   0.7173
  -2.000   0.1429   0.01676   0.01150  -0.0671   0.8196   0.7225
  -1.750   0.1664   0.01694   0.01160  -0.0648   0.8064   0.7292
  -1.500   0.1980   0.01674   0.01128  -0.0657   0.7882   0.7390
  -1.250   0.2192   0.01672   0.01121  -0.0631   0.7671   0.7423
  -1.000   0.2419   0.01670   0.01108  -0.0610   0.7401   0.7463
  -0.750   0.2662   0.01665   0.01088  -0.0597   0.6958   0.7521
  -0.500   0.2954   0.01667   0.01041  -0.0602   0.6034   0.7601
  -0.250   0.3099   0.01713   0.01040  -0.0567   0.5355   0.7634
   0.000   0.3290   0.01756   0.01054  -0.0545   0.5036   0.7676
   0.250   0.3537   0.01789   0.01064  -0.0539   0.4831   0.7732
   0.500   0.3887   0.01811   0.01066  -0.0563   0.4665   0.7802
   0.750   0.4091   0.01823   0.01072  -0.0543   0.4549   0.7832
   1.000   0.4321   0.01843   0.01081  -0.0530   0.4441   0.7865
   1.250   0.4586   0.01862   0.01091  -0.0528   0.4347   0.7904
   1.500   0.4887   0.01873   0.01095  -0.0536   0.4255   0.7946
   1.750   0.5236   0.01905   0.01106  -0.0558   0.4164   0.7989
   2.000   0.5496   0.01902   0.01107  -0.0554   0.4092   0.8017
   2.250   0.5744   0.01910   0.01114  -0.0547   0.4021   0.8042
   2.500   0.6015   0.01935   0.01126  -0.0547   0.3952   0.8067
   2.750   0.6298   0.01948   0.01140  -0.0549   0.3888   0.8097
   3.000   0.6599   0.01958   0.01149  -0.0557   0.3821   0.8126
   3.250   0.6919   0.01976   0.01160  -0.0570   0.3759   0.8150
   3.500   0.7263   0.02011   0.01185  -0.0590   0.3696   0.8180
   3.750   0.7533   0.02015   0.01195  -0.0590   0.3639   0.8202
   4.000   0.7797   0.02025   0.01205  -0.0588   0.3582   0.8221
   4.250   0.8074   0.02045   0.01219  -0.0589   0.3529   0.8240
   4.500   0.8360   0.02076   0.01248  -0.0594   0.3477   0.8260
   4.750   0.8640   0.02089   0.01268  -0.0596   0.3423   0.8287
   5.000   0.8934   0.02107   0.01286  -0.0603   0.3368   0.8316
   5.250   0.9248   0.02135   0.01306  -0.0614   0.3317   0.8339
   5.500   0.9570   0.02173   0.01345  -0.0628   0.3266   0.8361
   5.750   0.9840   0.02186   0.01365  -0.0630   0.3212   0.8380
   6.000   1.0100   0.02200   0.01381  -0.0628   0.3163   0.8399
   6.250   1.0367   0.02226   0.01402  -0.0628   0.3117   0.8422
   6.500   1.0632   0.02263   0.01443  -0.0628   0.3069   0.8450
   6.750   1.0898   0.02283   0.01473  -0.0629   0.3017   0.8479
   7.000   1.1184   0.02305   0.01496  -0.0634   0.2967   0.8504
   7.250   1.1491   0.02343   0.01524  -0.0645   0.2921   0.8529
   7.500   1.1757   0.02378   0.01569  -0.0647   0.2872   0.8552
   7.750   1.1988   0.02397   0.01599  -0.0640   0.2822   0.8575
   8.000   1.2236   0.02417   0.01619  -0.0637   0.2775   0.8601
   8.250   1.2513   0.02463   0.01655  -0.0640   0.2729   0.8630
   8.500   1.2741   0.02492   0.01703  -0.0635   0.2681   0.8665
   8.750   1.3002   0.02521   0.01738  -0.0637   0.2629   0.8700
   9.000   1.3241   0.02544   0.01758  -0.0633   0.2584   0.8728
   9.250   1.3469   0.02589   0.01807  -0.0628   0.2539   0.8758
   9.500   1.3670   0.02619   0.01853  -0.0618   0.2488   0.8792
   9.750   1.3903   0.02648   0.01883  -0.0614   0.2440   0.8829
  10.000   1.4181   0.02702   0.01927  -0.0620   0.2394   0.8864
  10.250   1.4322   0.02734   0.01982  -0.0600   0.2346   0.8900
  10.500   1.4502   0.02764   0.02020  -0.0587   0.2298   0.8941
  10.750   1.4728   0.02805   0.02053  -0.0583   0.2254   0.8985
  11.000   1.4882   0.02860   0.02124  -0.0567   0.2206   0.9032
  11.250   1.5005   0.02898   0.02173  -0.0545   0.2160   0.9087
  11.500   1.5169   0.02939   0.02212  -0.0531   0.2118   0.9144
  11.750   1.5282   0.02998   0.02280  -0.0509   0.2075   0.9199
  12.000   1.5369   0.03059   0.02357  -0.0485   0.2029   0.9266
  12.250   1.5491   0.03112   0.02412  -0.0467   0.1988   0.9334
  12.500   1.5618   0.03185   0.02486  -0.0450   0.1946   0.9415
  12.750   1.5657   0.03265   0.02585  -0.0423   0.1903   0.9520
  13.000   1.5733   0.03331   0.02658  -0.0401   0.1862   0.9674
  13.250   1.5868   0.03418   0.02742  -0.0392   0.1821   1.0000
  13.500   1.5949   0.03565   0.02910  -0.0385   0.1774   1.0000
  13.750   1.6080   0.03689   0.03036  -0.0383   0.1731   1.0000
  14.000   1.6204   0.03835   0.03185  -0.0380   0.1689   1.0000
  14.250   1.6260   0.04017   0.03384  -0.0374   0.1645   1.0000
  14.500   1.6365   0.04167   0.03534  -0.0371   0.1606   1.0000
  14.750   1.6427   0.04363   0.03738  -0.0367   0.1566   1.0000
  15.000   1.6447   0.04588   0.03977  -0.0362   0.1527   1.0000
  15.250   1.6522   0.04770   0.04158  -0.0360   0.1491   1.0000
  15.500   1.6532   0.05019   0.04417  -0.0356   0.1456   1.0000
  15.750   1.6504   0.05306   0.04719  -0.0354   0.1420   1.0000
  16.000   1.6538   0.05533   0.04947  -0.0352   0.1388   1.0000
  16.250   1.6531   0.05815   0.05235  -0.0352   0.1356   1.0000
  16.500   1.6442   0.06199   0.05639  -0.0356   0.1325   1.0000
  16.750   1.6432   0.06499   0.05942  -0.0360   0.1294   1.0000
  17.000   1.6437   0.06787   0.06229  -0.0363   0.1263   1.0000
  17.250   1.6277   0.07312   0.06778  -0.0378   0.1235   1.0000
  17.500   1.6219   0.07713   0.07187  -0.0390   0.1205   1.0000
  17.750   1.6265   0.07957   0.07423  -0.0395   0.1175   1.0000
  18.000   1.6034   0.08643   0.08136  -0.0423   0.1150   1.0000
  18.250   1.5923   0.09158   0.08664  -0.0445   0.1123   1.0000
  18.500   1.6021   0.09324   0.08817  -0.0448   0.1094   1.0000
  18.750   1.5775   0.10075   0.09594  -0.0484   0.1072   1.0000
  19.000   1.5593   0.10730   0.10266  -0.0517   0.1047   1.0000
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