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NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il)
Reynolds number: 100,000
Max Cl/Cd: 30.88 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls013-il-100000-n5.txt
Download as CSV file: xf-ls013-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8795   0.09111   0.08576  -0.0093   1.0000   0.0422
 -13.000  -0.9286   0.07897   0.07336  -0.0173   1.0000   0.0415
 -12.750  -0.9631   0.07113   0.06525  -0.0211   1.0000   0.0414
 -12.500  -0.9894   0.06529   0.05913  -0.0228   1.0000   0.0415
 -12.250  -1.0102   0.06056   0.05411  -0.0230   1.0000   0.0419
 -12.000  -1.0272   0.05655   0.04980  -0.0223   1.0000   0.0424
 -11.750  -1.0411   0.05305   0.04596  -0.0207   1.0000   0.0430
 -11.500  -1.0520   0.04994   0.04246  -0.0184   1.0000   0.0437
 -11.250  -1.0547   0.04694   0.03902  -0.0165   1.0000   0.0445
 -11.000  -1.0421   0.04486   0.03688  -0.0158   1.0000   0.0454
 -10.750  -1.0293   0.04297   0.03485  -0.0150   1.0000   0.0463
 -10.500  -1.0153   0.04110   0.03280  -0.0142   1.0000   0.0474
 -10.250  -1.0001   0.03931   0.03080  -0.0135   1.0000   0.0489
 -10.000  -0.9837   0.03751   0.02871  -0.0128   1.0000   0.0508
  -9.750  -0.9657   0.03571   0.02653  -0.0121   1.0000   0.0527
  -9.500  -0.9444   0.03407   0.02489  -0.0119   1.0000   0.0543
  -9.250  -0.9227   0.03273   0.02351  -0.0117   1.0000   0.0560
  -9.000  -0.9006   0.03150   0.02215  -0.0115   1.0000   0.0584
  -8.750  -0.8778   0.03029   0.02074  -0.0112   1.0000   0.0613
  -8.500  -0.8544   0.02900   0.01937  -0.0111   1.0000   0.0639
  -8.250  -0.8314   0.02791   0.01831  -0.0110   1.0000   0.0664
  -8.000  -0.8081   0.02695   0.01729  -0.0109   1.0000   0.0699
  -7.750  -0.7840   0.02606   0.01625  -0.0107   1.0000   0.0737
  -7.500  -0.7620   0.02502   0.01528  -0.0105   1.0000   0.0771
  -7.250  -0.7399   0.02422   0.01448  -0.0102   1.0000   0.0815
  -7.000  -0.7181   0.02352   0.01367  -0.0097   1.0000   0.0863
  -6.750  -0.7010   0.02270   0.01294  -0.0086   1.0000   0.0907
  -6.500  -0.6717   0.02198   0.01217  -0.0097   0.9856   0.0981
  -6.250  -0.6422   0.02116   0.01139  -0.0109   0.9759   0.1067
  -6.000  -0.6114   0.02042   0.01065  -0.0122   0.9684   0.1177
  -5.750  -0.5830   0.01971   0.01000  -0.0130   0.9602   0.1334
  -5.500  -0.5540   0.01900   0.00938  -0.0139   0.9536   0.1574
  -5.250  -0.5288   0.01826   0.00886  -0.0141   0.9457   0.1932
  -5.000  -0.5040   0.01744   0.00838  -0.0144   0.9393   0.2569
  -4.750  -0.4822   0.01662   0.00798  -0.0140   0.9315   0.3393
  -4.250  -0.4398   0.01550   0.00797  -0.0116   0.9185   0.5459
  -4.000  -0.4147   0.01564   0.00826  -0.0105   0.9129   0.6106
  -3.750  -0.3889   0.01581   0.00841  -0.0097   0.9072   0.6491
  -3.500  -0.3632   0.01603   0.00859  -0.0088   0.9011   0.6771
  -3.250  -0.3374   0.01624   0.00874  -0.0080   0.8962   0.7017
  -3.000  -0.3120   0.01657   0.00904  -0.0069   0.8910   0.7212
  -2.750  -0.2871   0.01693   0.00937  -0.0055   0.8855   0.7399
  -2.500  -0.2622   0.01723   0.00963  -0.0042   0.8809   0.7554
  -2.250  -0.2363   0.01736   0.00969  -0.0037   0.8761   0.7674
  -2.000  -0.2099   0.01751   0.00981  -0.0030   0.8710   0.7753
  -1.750  -0.1837   0.01755   0.00978  -0.0027   0.8663   0.7842
  -1.500  -0.1575   0.01765   0.00983  -0.0020   0.8624   0.7909
  -1.250  -0.1310   0.01768   0.00983  -0.0020   0.8570   0.7998
  -1.000  -0.1055   0.01784   0.00998  -0.0011   0.8522   0.8077
  -0.750  -0.0801   0.01790   0.01001  -0.0003   0.8482   0.8171
  -0.500  -0.0538   0.01798   0.01010   0.0000   0.8433   0.8233
  -0.250  -0.0269   0.01796   0.01005  -0.0002   0.8381   0.8295
   0.000   0.0000   0.01794   0.01003   0.0000   0.8338   0.8337
   0.250   0.0269   0.01796   0.01005   0.0002   0.8295   0.8381
   0.500   0.0538   0.01798   0.01010   0.0000   0.8233   0.8433
   0.750   0.0801   0.01790   0.01001   0.0003   0.8171   0.8482
   1.000   0.1055   0.01784   0.00998   0.0011   0.8077   0.8522
   1.250   0.1310   0.01768   0.00983   0.0020   0.7998   0.8570
   1.500   0.1575   0.01765   0.00983   0.0020   0.7909   0.8624
   1.750   0.1837   0.01755   0.00978   0.0027   0.7842   0.8663
   2.000   0.2099   0.01751   0.00981   0.0030   0.7753   0.8710
   2.250   0.2363   0.01736   0.00969   0.0037   0.7674   0.8761
   2.500   0.2622   0.01723   0.00963   0.0042   0.7554   0.8809
   2.750   0.2871   0.01693   0.00937   0.0055   0.7399   0.8855
   3.000   0.3120   0.01657   0.00903   0.0069   0.7212   0.8910
   3.250   0.3374   0.01624   0.00874   0.0080   0.7016   0.8962
   3.500   0.3632   0.01603   0.00859   0.0088   0.6771   0.9011
   3.750   0.3889   0.01581   0.00841   0.0097   0.6491   0.9072
   4.000   0.4147   0.01564   0.00826   0.0105   0.6106   0.9129
   4.250   0.4398   0.01550   0.00797   0.0116   0.5457   0.9185
   4.750   0.4822   0.01662   0.00797   0.0140   0.3393   0.9315
   5.000   0.5040   0.01744   0.00838   0.0144   0.2568   0.9393
   5.250   0.5288   0.01826   0.00886   0.0141   0.1932   0.9457
   5.500   0.5541   0.01899   0.00938   0.0139   0.1573   0.9536
   5.750   0.5830   0.01971   0.01000   0.0130   0.1334   0.9602
   6.000   0.6114   0.02042   0.01065   0.0122   0.1177   0.9684
   6.250   0.6423   0.02116   0.01139   0.0109   0.1067   0.9760
   6.500   0.6717   0.02198   0.01217   0.0097   0.0981   0.9856
   6.750   0.7009   0.02270   0.01294   0.0086   0.0907   1.0000
   7.000   0.7182   0.02351   0.01367   0.0097   0.0863   1.0000
   7.250   0.7399   0.02422   0.01448   0.0102   0.0815   1.0000
   7.500   0.7620   0.02502   0.01528   0.0105   0.0771   1.0000
   7.750   0.7841   0.02606   0.01625   0.0107   0.0737   1.0000
   8.000   0.8082   0.02695   0.01729   0.0108   0.0699   1.0000
   8.250   0.8316   0.02791   0.01831   0.0110   0.0664   1.0000
   8.500   0.8546   0.02900   0.01937   0.0111   0.0639   1.0000
   8.750   0.8780   0.03029   0.02075   0.0112   0.0613   1.0000
   9.000   0.9008   0.03150   0.02215   0.0114   0.0584   1.0000
   9.250   0.9229   0.03273   0.02351   0.0117   0.0560   1.0000
   9.500   0.9446   0.03407   0.02489   0.0119   0.0543   1.0000
   9.750   0.9660   0.03571   0.02653   0.0120   0.0527   1.0000
  10.000   0.9839   0.03751   0.02872   0.0127   0.0508   1.0000
  10.250   1.0003   0.03931   0.03081   0.0135   0.0488   1.0000
  10.500   1.0156   0.04110   0.03281   0.0142   0.0473   1.0000
  10.750   1.0296   0.04298   0.03486   0.0150   0.0463   1.0000
  11.000   1.0425   0.04487   0.03689   0.0157   0.0454   1.0000
  11.250   1.0551   0.04695   0.03903   0.0164   0.0445   1.0000
  11.500   1.0523   0.04996   0.04248   0.0183   0.0437   1.0000
  11.750   1.0415   0.05308   0.04599   0.0206   0.0430   1.0000
  12.000   1.0276   0.05659   0.04984   0.0222   0.0423   1.0000
  12.250   1.0107   0.06060   0.05416   0.0229   0.0419   1.0000
  12.500   0.9899   0.06533   0.05918   0.0226   0.0415   1.0000
  12.750   0.9637   0.07120   0.06532   0.0209   0.0414   1.0000
  13.000   0.9290   0.07908   0.07347   0.0171   0.0415   1.0000
  13.250   0.8794   0.09139   0.08605   0.0089   0.0422   1.0000
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