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NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il)
Reynolds number: 200,000
Max Cl/Cd: 62.04 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls413mod-il-200000-n5.txt
Download as CSV file: xf-ls413mod-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0413MOD 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6381   0.06309   0.05869  -0.0624   1.0000   0.0243
 -11.500  -0.6588   0.05760   0.05305  -0.0657   1.0000   0.0242
 -11.250  -0.6785   0.05339   0.04869  -0.0667   1.0000   0.0242
 -11.000  -0.6993   0.05029   0.04546  -0.0654   1.0000   0.0241
 -10.750  -0.7137   0.04716   0.04214  -0.0643   1.0000   0.0241
 -10.500  -0.7227   0.04425   0.03900  -0.0625   1.0000   0.0241
 -10.250  -0.7273   0.04153   0.03601  -0.0606   1.0000   0.0241
 -10.000  -0.7276   0.03904   0.03326  -0.0586   1.0000   0.0242
  -9.750  -0.7165   0.03637   0.03024  -0.0586   0.9984   0.0242
  -9.500  -0.6901   0.03352   0.02700  -0.0610   0.9945   0.0244
  -9.250  -0.6626   0.03113   0.02436  -0.0630   0.9906   0.0246
  -9.000  -0.6329   0.02919   0.02222  -0.0649   0.9866   0.0249
  -8.750  -0.6008   0.02751   0.02036  -0.0670   0.9833   0.0251
  -8.500  -0.5701   0.02612   0.01883  -0.0686   0.9788   0.0256
  -8.250  -0.5381   0.02490   0.01747  -0.0703   0.9745   0.0262
  -8.000  -0.5045   0.02373   0.01616  -0.0722   0.9713   0.0269
  -7.750  -0.4726   0.02260   0.01488  -0.0736   0.9672   0.0275
  -7.500  -0.4420   0.02153   0.01369  -0.0745   0.9617   0.0280
  -7.250  -0.4090   0.02051   0.01256  -0.0759   0.9576   0.0285
  -7.000  -0.3769   0.01962   0.01158  -0.0771   0.9529   0.0290
  -6.750  -0.3469   0.01873   0.01066  -0.0780   0.9465   0.0295
  -6.500  -0.3142   0.01785   0.00979  -0.0795   0.9418   0.0304
  -6.250  -0.2834   0.01718   0.00912  -0.0805   0.9352   0.0313
  -6.000  -0.2519   0.01655   0.00847  -0.0816   0.9286   0.0324
  -5.750  -0.2190   0.01600   0.00786  -0.0829   0.9232   0.0342
  -5.500  -0.1891   0.01545   0.00731  -0.0836   0.9151   0.0363
  -5.250  -0.1566   0.01497   0.00681  -0.0848   0.9092   0.0388
  -4.750  -0.0952   0.01412   0.00591  -0.0863   0.8941   0.0467
  -4.500  -0.0649   0.01371   0.00552  -0.0870   0.8862   0.0572
  -4.250  -0.0339   0.01321   0.00513  -0.0879   0.8786   0.0831
  -4.000  -0.0028   0.01261   0.00480  -0.0891   0.8708   0.1427
  -3.750   0.0294   0.01185   0.00447  -0.0908   0.8629   0.2517
  -3.500   0.0632   0.01094   0.00422  -0.0930   0.8553   0.4111
  -3.250   0.0941   0.01049   0.00425  -0.0938   0.8468   0.5354
  -3.000   0.1221   0.01047   0.00443  -0.0934   0.8383   0.6102
  -2.750   0.1503   0.01056   0.00455  -0.0930   0.8292   0.6521
  -2.500   0.1788   0.01068   0.00463  -0.0928   0.8200   0.6801
  -2.250   0.2062   0.01081   0.00472  -0.0922   0.8113   0.6986
  -2.000   0.2345   0.01091   0.00479  -0.0920   0.8021   0.7125
  -1.750   0.2616   0.01100   0.00483  -0.0914   0.7941   0.7206
  -1.500   0.2907   0.01107   0.00485  -0.0915   0.7851   0.7310
  -1.250   0.3176   0.01116   0.00491  -0.0909   0.7773   0.7377
  -1.000   0.3470   0.01120   0.00489  -0.0912   0.7680   0.7433
  -0.750   0.3766   0.01123   0.00484  -0.0914   0.7597   0.7482
  -0.500   0.4039   0.01129   0.00490  -0.0910   0.7495   0.7528
  -0.250   0.4323   0.01135   0.00491  -0.0909   0.7382   0.7586
   0.000   0.4615   0.01140   0.00488  -0.0911   0.7251   0.7644
   0.250   0.4884   0.01146   0.00489  -0.0906   0.7107   0.7681
   0.500   0.5162   0.01153   0.00491  -0.0904   0.6966   0.7723
   0.750   0.5453   0.01159   0.00493  -0.0905   0.6830   0.7773
   1.000   0.5741   0.01166   0.00497  -0.0907   0.6699   0.7816
   1.250   0.6010   0.01175   0.00501  -0.0903   0.6527   0.7848
   1.500   0.6283   0.01185   0.00503  -0.0900   0.6314   0.7882
   1.750   0.6563   0.01197   0.00507  -0.0900   0.6089   0.7921
   2.000   0.6853   0.01210   0.00512  -0.0902   0.5880   0.7965
   2.250   0.7115   0.01225   0.00522  -0.0898   0.5660   0.7993
   2.500   0.7378   0.01243   0.00532  -0.0894   0.5417   0.8026
   2.750   0.7642   0.01265   0.00545  -0.0891   0.5155   0.8065
   3.000   0.7912   0.01292   0.00560  -0.0890   0.4867   0.8108
   3.250   0.8167   0.01322   0.00578  -0.0886   0.4560   0.8145
   3.500   0.8409   0.01356   0.00600  -0.0879   0.4246   0.8177
   3.750   0.8654   0.01395   0.00626  -0.0874   0.3920   0.8213
   4.000   0.8900   0.01439   0.00654  -0.0870   0.3566   0.8255
   4.250   0.9144   0.01488   0.00686  -0.0866   0.3210   0.8297
   4.500   0.9367   0.01536   0.00721  -0.0858   0.2894   0.8330
   4.750   0.9598   0.01586   0.00759  -0.0851   0.2619   0.8368
   5.000   0.9838   0.01634   0.00799  -0.0847   0.2388   0.8410
   5.250   1.0081   0.01684   0.00840  -0.0843   0.2177   0.8455
   5.500   1.0301   0.01730   0.00882  -0.0834   0.2005   0.8492
   5.750   1.0530   0.01776   0.00925  -0.0827   0.1860   0.8536
   6.000   1.0768   0.01824   0.00971  -0.0823   0.1736   0.8582
   6.250   1.0993   0.01873   0.01019  -0.0815   0.1633   0.8623
   6.500   1.1208   0.01919   0.01066  -0.0806   0.1543   0.8668
   6.750   1.1429   0.01969   0.01118  -0.0798   0.1471   0.8721
   7.000   1.1646   0.02021   0.01172  -0.0790   0.1402   0.8771
   7.250   1.1843   0.02074   0.01228  -0.0777   0.1345   0.8818
   7.500   1.2055   0.02124   0.01285  -0.0768   0.1289   0.8873
   7.750   1.2247   0.02184   0.01346  -0.0756   0.1242   0.8929
   8.000   1.2426   0.02242   0.01409  -0.0741   0.1204   0.8991
   8.250   1.2629   0.02295   0.01473  -0.0731   0.1161   0.9057
   8.500   1.2793   0.02351   0.01533  -0.0714   0.1115   0.9123
   9.000   1.3119   0.02463   0.01660  -0.0681   0.1025   0.9284
   9.250   1.3242   0.02517   0.01720  -0.0658   0.0983   0.9398
   9.750   1.3501   0.02645   0.01863  -0.0618   0.0916   1.0000
  10.000   1.3681   0.02726   0.01952  -0.0611   0.0880   1.0000
  10.250   1.3839   0.02820   0.02051  -0.0601   0.0847   1.0000
  10.500   1.3989   0.02922   0.02158  -0.0591   0.0817   1.0000
  10.750   1.4153   0.03013   0.02262  -0.0582   0.0783   1.0000
  11.000   1.4296   0.03119   0.02375  -0.0573   0.0750   1.0000
  11.250   1.4410   0.03247   0.02507  -0.0562   0.0721   1.0000
  11.500   1.4546   0.03363   0.02636  -0.0552   0.0692   1.0000
  11.750   1.4671   0.03488   0.02773  -0.0543   0.0657   1.0000
  12.000   1.4765   0.03638   0.02928  -0.0533   0.0625   1.0000
  12.250   1.4863   0.03792   0.03092  -0.0524   0.0593   1.0000
  12.500   1.4958   0.03951   0.03263  -0.0515   0.0558   1.0000
  12.750   1.5016   0.04146   0.03464  -0.0507   0.0528   1.0000
  13.000   1.5083   0.04340   0.03671  -0.0499   0.0498   1.0000
  13.250   1.5137   0.04551   0.03894  -0.0493   0.0470   1.0000
  13.500   1.5160   0.04797   0.04147  -0.0487   0.0448   1.0000
  13.750   1.5177   0.05058   0.04419  -0.0483   0.0429   1.0000
  14.000   1.5190   0.05330   0.04705  -0.0479   0.0411   1.0000
  14.250   1.5184   0.05630   0.05017  -0.0478   0.0395   1.0000
  14.500   1.5156   0.05964   0.05362  -0.0479   0.0383   1.0000
  14.750   1.5101   0.06345   0.05753  -0.0483   0.0373   1.0000
  15.000   1.5059   0.06722   0.06145  -0.0488   0.0363   1.0000
  15.250   1.5006   0.07128   0.06566  -0.0496   0.0354   1.0000
  15.500   1.4941   0.07565   0.07018  -0.0506   0.0346   1.0000
  15.750   1.4862   0.08039   0.07506  -0.0520   0.0339   1.0000
  16.000   1.4767   0.08548   0.08030  -0.0537   0.0333   1.0000
  16.250   1.4657   0.09098   0.08593  -0.0558   0.0327   1.0000
  16.500   1.4537   0.09681   0.09188  -0.0582   0.0323   1.0000
  16.750   1.4407   0.10292   0.09812  -0.0608   0.0319   1.0000
  17.000   1.4272   0.10918   0.10448  -0.0637   0.0315   1.0000
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