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NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il)
Reynolds number: 200,000
Max Cl/Cd: 39.94 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls013-il-200000-n5.txt
Download as CSV file: xf-ls013-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0013 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
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -1.0364   0.09867   0.09453   0.0012   1.0000   0.0256
 -15.500  -1.0720   0.08714   0.08274  -0.0064   1.0000   0.0255
 -15.250  -1.1007   0.07823   0.07357  -0.0118   1.0000   0.0255
 -15.000  -1.1248   0.07103   0.06609  -0.0155   1.0000   0.0256
 -14.750  -1.1449   0.06501   0.05978  -0.0180   1.0000   0.0258
 -14.500  -1.1523   0.06107   0.05573  -0.0191   1.0000   0.0260
 -14.250  -1.1564   0.05774   0.05230  -0.0197   1.0000   0.0263
 -14.000  -1.1589   0.05473   0.04918  -0.0201   1.0000   0.0266
 -13.750  -1.1603   0.05194   0.04626  -0.0202   1.0000   0.0269
 -13.500  -1.1608   0.04932   0.04350  -0.0200   1.0000   0.0272
 -13.250  -1.1603   0.04687   0.04091  -0.0196   1.0000   0.0276
 -13.000  -1.1585   0.04460   0.03846  -0.0190   1.0000   0.0281
 -12.750  -1.1557   0.04246   0.03615  -0.0182   1.0000   0.0287
 -12.500  -1.1515   0.04042   0.03388  -0.0172   1.0000   0.0294
 -12.250  -1.1459   0.03846   0.03168  -0.0161   1.0000   0.0301
 -12.000  -1.1384   0.03666   0.02963  -0.0149   1.0000   0.0308
 -11.750  -1.1280   0.03505   0.02791  -0.0137   1.0000   0.0314
 -11.500  -1.1160   0.03376   0.02657  -0.0126   1.0000   0.0320
 -11.250  -1.1033   0.03262   0.02536  -0.0114   1.0000   0.0326
 -11.000  -1.0879   0.03150   0.02414  -0.0105   1.0000   0.0335
 -10.750  -1.0708   0.03041   0.02294  -0.0097   1.0000   0.0345
 -10.500  -1.0524   0.02931   0.02169  -0.0091   1.0000   0.0358
 -10.250  -1.0327   0.02826   0.02045  -0.0085   1.0000   0.0369
 -10.000  -1.0134   0.02707   0.01924  -0.0080   1.0000   0.0380
  -9.750  -0.9929   0.02613   0.01827  -0.0076   1.0000   0.0391
  -9.500  -0.9714   0.02526   0.01735  -0.0073   1.0000   0.0404
  -9.250  -0.9489   0.02441   0.01644  -0.0071   1.0000   0.0420
  -9.000  -0.9256   0.02364   0.01555  -0.0070   1.0000   0.0438
  -8.750  -0.9030   0.02272   0.01460  -0.0069   1.0000   0.0455
  -8.500  -0.8765   0.02202   0.01388  -0.0076   0.9635   0.0475
  -8.250  -0.8512   0.02138   0.01317  -0.0077   0.9490   0.0496
  -8.000  -0.8277   0.02082   0.01250  -0.0073   0.9374   0.0519
  -7.750  -0.8062   0.02019   0.01181  -0.0065   0.9272   0.0542
  -7.500  -0.7838   0.01964   0.01125  -0.0060   0.9187   0.0569
  -7.250  -0.7613   0.01917   0.01071  -0.0053   0.9113   0.0598
  -7.000  -0.7372   0.01873   0.01017  -0.0048   0.9042   0.0627
  -6.750  -0.7153   0.01813   0.00960  -0.0041   0.8974   0.0664
  -6.500  -0.6914   0.01769   0.00911  -0.0037   0.8914   0.0707
  -6.250  -0.6670   0.01725   0.00863  -0.0033   0.8854   0.0754
  -6.000  -0.6435   0.01679   0.00816  -0.0028   0.8804   0.0813
  -5.750  -0.6183   0.01638   0.00773  -0.0026   0.8751   0.0881
  -5.500  -0.5932   0.01594   0.00731  -0.0024   0.8696   0.0978
  -5.250  -0.5686   0.01552   0.00691  -0.0020   0.8649   0.1104
  -5.000  -0.5430   0.01510   0.00655  -0.0019   0.8605   0.1276
  -4.750  -0.5171   0.01462   0.00618  -0.0019   0.8556   0.1527
  -4.500  -0.4922   0.01409   0.00582  -0.0018   0.8511   0.1918
  -4.250  -0.4680   0.01348   0.00546  -0.0016   0.8473   0.2501
  -4.000  -0.4422   0.01286   0.00515  -0.0018   0.8425   0.3168
  -3.750  -0.4167   0.01225   0.00484  -0.0018   0.8382   0.3865
  -3.500  -0.3929   0.01153   0.00462  -0.0015   0.8344   0.4872
  -3.000  -0.3404   0.01116   0.00478  -0.0006   0.8264   0.6290
  -2.750  -0.3122   0.01117   0.00481  -0.0005   0.8223   0.6560
  -2.500  -0.2842   0.01121   0.00485  -0.0003   0.8188   0.6770
  -2.250  -0.2565   0.01128   0.00490   0.0000   0.8156   0.6964
  -2.000  -0.2280   0.01137   0.00500   0.0000   0.8115   0.7158
  -1.750  -0.1999   0.01147   0.00512   0.0002   0.8073   0.7303
  -1.500  -0.1716   0.01152   0.00516   0.0003   0.8037   0.7387
  -1.250  -0.1430   0.01154   0.00514   0.0002   0.8005   0.7463
  -1.000  -0.1145   0.01158   0.00516   0.0002   0.7970   0.7530
  -0.750  -0.0855   0.01163   0.00523   0.0000   0.7928   0.7606
  -0.500  -0.0567   0.01167   0.00526  -0.0001   0.7889   0.7680
  -0.250  -0.0288   0.01172   0.00532   0.0001   0.7853   0.7745
   0.000   0.0000   0.01173   0.00529   0.0000   0.7814   0.7814
   0.250   0.0287   0.01172   0.00532  -0.0001   0.7745   0.7852
   0.500   0.0566   0.01167   0.00526   0.0001   0.7680   0.7889
   0.750   0.0855   0.01163   0.00523   0.0000   0.7606   0.7928
   1.000   0.1145   0.01158   0.00516  -0.0002   0.7531   0.7970
   1.250   0.1430   0.01154   0.00514  -0.0002   0.7464   0.8005
   1.500   0.1716   0.01152   0.00516  -0.0003   0.7386   0.8037
   1.750   0.1999   0.01147   0.00512  -0.0002   0.7303   0.8073
   2.000   0.2280   0.01137   0.00500   0.0000   0.7159   0.8115
   2.250   0.2565   0.01128   0.00490   0.0000   0.6964   0.8156
   2.500   0.2842   0.01121   0.00485   0.0003   0.6770   0.8188
   2.750   0.3122   0.01117   0.00481   0.0005   0.6560   0.8223
   3.000   0.3404   0.01116   0.00478   0.0006   0.6291   0.8264
   3.500   0.3929   0.01153   0.00462   0.0015   0.4870   0.8344
   3.750   0.4167   0.01225   0.00484   0.0018   0.3863   0.8382
   4.000   0.4422   0.01287   0.00515   0.0018   0.3167   0.8425
   4.250   0.4680   0.01348   0.00546   0.0016   0.2501   0.8473
   4.500   0.4922   0.01409   0.00582   0.0018   0.1918   0.8511
   4.750   0.5172   0.01462   0.00618   0.0019   0.1527   0.8556
   5.000   0.5430   0.01510   0.00655   0.0019   0.1276   0.8605
   5.250   0.5686   0.01552   0.00691   0.0020   0.1104   0.8649
   5.500   0.5933   0.01594   0.00731   0.0023   0.0978   0.8695
   5.750   0.6184   0.01638   0.00773   0.0025   0.0881   0.8751
   6.000   0.6436   0.01679   0.00816   0.0028   0.0812   0.8804
   6.250   0.6670   0.01725   0.00863   0.0033   0.0753   0.8854
   6.500   0.6915   0.01769   0.00912   0.0037   0.0706   0.8914
   6.750   0.7154   0.01813   0.00960   0.0041   0.0664   0.8974
   7.000   0.7373   0.01873   0.01017   0.0048   0.0627   0.9042
   7.250   0.7614   0.01917   0.01071   0.0052   0.0598   0.9113
   7.500   0.7840   0.01964   0.01125   0.0059   0.0569   0.9187
   7.750   0.8063   0.02019   0.01182   0.0065   0.0542   0.9272
   8.000   0.8279   0.02082   0.01250   0.0072   0.0519   0.9374
   8.250   0.8514   0.02138   0.01317   0.0076   0.0496   0.9490
   8.500   0.8766   0.02202   0.01388   0.0075   0.0475   0.9634
   8.750   0.9032   0.02271   0.01460   0.0069   0.0455   1.0000
   9.000   0.9257   0.02363   0.01555   0.0070   0.0438   1.0000
   9.250   0.9491   0.02441   0.01644   0.0071   0.0420   1.0000
   9.500   0.9716   0.02526   0.01735   0.0073   0.0404   1.0000
   9.750   0.9931   0.02613   0.01827   0.0076   0.0391   1.0000
  10.000   1.0136   0.02708   0.01925   0.0079   0.0380   1.0000
  10.250   1.0330   0.02826   0.02046   0.0084   0.0369   1.0000
  10.500   1.0528   0.02931   0.02170   0.0090   0.0358   1.0000
  10.750   1.0712   0.03041   0.02294   0.0097   0.0345   1.0000
  11.000   1.0883   0.03150   0.02415   0.0104   0.0334   1.0000
  11.250   1.1038   0.03262   0.02537   0.0113   0.0326   1.0000
  11.500   1.1166   0.03376   0.02658   0.0125   0.0320   1.0000
  11.750   1.1286   0.03505   0.02791   0.0136   0.0314   1.0000
  12.000   1.1390   0.03667   0.02964   0.0147   0.0308   1.0000
  12.250   1.1466   0.03847   0.03170   0.0160   0.0301   1.0000
  12.500   1.1523   0.04042   0.03389   0.0171   0.0294   1.0000
  12.750   1.1565   0.04247   0.03616   0.0181   0.0287   1.0000
  13.000   1.1594   0.04460   0.03847   0.0189   0.0281   1.0000
  13.250   1.1613   0.04686   0.04089   0.0195   0.0276   1.0000
  13.500   1.1619   0.04931   0.04349   0.0199   0.0272   1.0000
  13.750   1.1614   0.05193   0.04625   0.0200   0.0269   1.0000
  14.000   1.1601   0.05472   0.04916   0.0199   0.0266   1.0000
  14.250   1.1579   0.05769   0.05224   0.0195   0.0263   1.0000
  14.500   1.1538   0.06103   0.05569   0.0189   0.0260   1.0000
  14.750   1.1458   0.06507   0.05985   0.0178   0.0258   1.0000
  15.000   1.1257   0.07111   0.06618   0.0153   0.0256   1.0000
  15.250   1.1016   0.07835   0.07369   0.0115   0.0255   1.0000
  15.500   1.0727   0.08732   0.08293   0.0060   0.0255   1.0000
  15.750   1.0369   0.09893   0.09480  -0.0017   0.0256   1.0000
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