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NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il)
Reynolds number: 50,000
Max Cl/Cd: 24.97 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls417-il-50000-n5.txt
Download as CSV file: xf-ls417-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4887   0.09801   0.09001  -0.0707   1.0000   0.0593
 -12.250  -0.5196   0.09088   0.08288  -0.0734   1.0000   0.0588
 -12.000  -0.5557   0.08487   0.07686  -0.0746   1.0000   0.0583
 -11.750  -0.5933   0.08031   0.07226  -0.0740   1.0000   0.0579
 -11.500  -0.6308   0.07679   0.06869  -0.0719   1.0000   0.0575
 -11.250  -0.6676   0.07397   0.06580  -0.0688   1.0000   0.0572
 -11.000  -0.7036   0.07166   0.06341  -0.0648   1.0000   0.0570
 -10.750  -0.7384   0.06978   0.06145  -0.0601   1.0000   0.0567
 -10.500  -0.7671   0.06753   0.05907  -0.0563   1.0000   0.0566
 -10.250  -0.7729   0.06363   0.05482  -0.0569   0.9948   0.0569
 -10.000  -0.7705   0.05989   0.05068  -0.0578   0.9891   0.0576
  -9.750  -0.7642   0.05637   0.04666  -0.0586   0.9837   0.0588
  -9.500  -0.7501   0.05371   0.04369  -0.0592   0.9797   0.0602
  -9.250  -0.7332   0.05195   0.04183  -0.0593   0.9754   0.0618
  -9.000  -0.7139   0.04985   0.03948  -0.0597   0.9713   0.0636
  -8.750  -0.6906   0.04761   0.03685  -0.0605   0.9680   0.0655
  -8.500  -0.6693   0.04587   0.03490  -0.0603   0.9643   0.0671
  -8.250  -0.6478   0.04462   0.03362  -0.0601   0.9604   0.0693
  -8.000  -0.6241   0.04335   0.03215  -0.0600   0.9572   0.0728
  -7.750  -0.5986   0.04228   0.03106  -0.0602   0.9545   0.0764
  -7.500  -0.5702   0.04129   0.02993  -0.0606   0.9521   0.0810
  -7.250  -0.5512   0.04049   0.02916  -0.0594   0.9482   0.0852
  -7.000  -0.5296   0.03974   0.02831  -0.0585   0.9443   0.0918
  -6.750  -0.5066   0.03895   0.02753  -0.0583   0.9407   0.0996
  -6.500  -0.4826   0.03810   0.02670  -0.0584   0.9377   0.1103
  -6.250  -0.4579   0.03720   0.02584  -0.0588   0.9353   0.1257
  -6.000  -0.4456   0.03630   0.02511  -0.0573   0.9311   0.1417
  -5.750  -0.4287   0.03530   0.02430  -0.0568   0.9269   0.1691
  -5.500  -0.4083   0.03396   0.02344  -0.0576   0.9232   0.2197
  -5.250  -0.3847   0.03247   0.02268  -0.0591   0.9202   0.3152
  -5.000  -0.3617   0.03194   0.02292  -0.0585   0.9177   0.4250
  -4.750  -0.3504   0.03275   0.02416  -0.0536   0.9138   0.4966
  -4.500  -0.3365   0.03378   0.02530  -0.0494   0.9090   0.5529
  -4.250  -0.3130   0.03458   0.02593  -0.0484   0.9049   0.6069
  -4.000  -0.2879   0.03550   0.02665  -0.0474   0.9015   0.6435
  -3.750  -0.2626   0.03647   0.02748  -0.0456   0.8985   0.6659
  -3.500  -0.2489   0.03717   0.02806  -0.0424   0.8938   0.6854
  -3.250  -0.2346   0.03784   0.02863  -0.0392   0.8891   0.7044
  -3.000  -0.2163   0.03849   0.02917  -0.0366   0.8851   0.7230
  -2.750  -0.1932   0.03898   0.02953  -0.0350   0.8815   0.7404
  -2.500  -0.1661   0.03931   0.02971  -0.0345   0.8785   0.7551
  -2.250  -0.1550   0.03955   0.02988  -0.0313   0.8736   0.7649
  -2.000  -0.1373   0.03965   0.02987  -0.0301   0.8685   0.7763
  -1.750  -0.1148   0.03978   0.02989  -0.0293   0.8642   0.7864
  -1.500  -0.0879   0.03988   0.02988  -0.0294   0.8605   0.7961
  -1.250  -0.0581   0.04000   0.02987  -0.0302   0.8573   0.8068
  -1.000  -0.0507   0.04010   0.02994  -0.0270   0.8504   0.8149
  -0.750  -0.0274   0.04020   0.02996  -0.0271   0.8452   0.8246
  -0.500  -0.0013   0.04023   0.02992  -0.0268   0.8409   0.8316
  -0.250   0.0323   0.04031   0.02990  -0.0284   0.8374   0.8393
   0.000   0.0394   0.04044   0.03003  -0.0257   0.8291   0.8460
   0.250   0.0649   0.04052   0.03005  -0.0259   0.8234   0.8523
   0.500   0.0997   0.04062   0.03009  -0.0279   0.8191   0.8584
   0.750   0.1152   0.04076   0.03022  -0.0264   0.8114   0.8636
   1.000   0.1391   0.04089   0.03033  -0.0265   0.8044   0.8689
   1.250   0.1748   0.04098   0.03038  -0.0285   0.7995   0.8736
   1.500   0.1922   0.04120   0.03062  -0.0277   0.7911   0.8781
   1.750   0.2181   0.04133   0.03074  -0.0280   0.7836   0.8826
   2.000   0.2561   0.04134   0.03075  -0.0301   0.7787   0.8865
   2.500   0.3044   0.04166   0.03113  -0.0303   0.7610   0.8945
   2.750   0.3256   0.04187   0.03137  -0.0300   0.7508   0.8988
   3.000   0.3587   0.04182   0.03135  -0.0312   0.7423   0.9023
   3.250   0.3834   0.04196   0.03154  -0.0313   0.7315   0.9060
   3.500   0.4157   0.04169   0.03133  -0.0320   0.7226   0.9097
   3.750   0.4370   0.04179   0.03149  -0.0314   0.7098   0.9142
   4.000   0.4779   0.04115   0.03092  -0.0330   0.7018   0.9178
   4.250   0.4971   0.04122   0.03108  -0.0321   0.6869   0.9217
   4.500   0.5218   0.04105   0.03099  -0.0318   0.6735   0.9256
   4.750   0.5622   0.03999   0.03003  -0.0326   0.6641   0.9296
   5.000   0.5841   0.03972   0.02985  -0.0317   0.6474   0.9346
   5.250   0.6078   0.03924   0.02947  -0.0308   0.6304   0.9400
   5.500   0.6328   0.03872   0.02907  -0.0301   0.6127   0.9456
   5.750   0.6576   0.03817   0.02863  -0.0294   0.5945   0.9511
   6.250   0.7137   0.03674   0.02742  -0.0284   0.5553   0.9635
   6.500   0.7377   0.03642   0.02719  -0.0278   0.5284   0.9719
   7.000   0.8008   0.03422   0.02487  -0.0266   0.4648   1.0000
   7.250   0.8331   0.03380   0.02416  -0.0265   0.4240   1.0000
   7.500   0.8561   0.03429   0.02437  -0.0261   0.3840   1.0000
   7.750   0.8742   0.03528   0.02513  -0.0257   0.3483   1.0000
   8.000   0.8909   0.03650   0.02616  -0.0254   0.3180   1.0000
   8.250   0.9077   0.03779   0.02726  -0.0251   0.2929   1.0000
   8.500   0.9249   0.03913   0.02842  -0.0250   0.2718   1.0000
   8.750   0.9434   0.04045   0.02964  -0.0251   0.2536   1.0000
   9.000   0.9630   0.04175   0.03089  -0.0253   0.2375   1.0000
   9.250   0.9838   0.04302   0.03213  -0.0255   0.2234   1.0000
   9.500   1.0061   0.04424   0.03332  -0.0258   0.2116   1.0000
   9.750   1.0293   0.04539   0.03440  -0.0262   0.2013   1.0000
  10.000   1.0530   0.04664   0.03574  -0.0266   0.1913   1.0000
  10.250   1.0799   0.04766   0.03666  -0.0272   0.1833   1.0000
  10.500   1.1030   0.04903   0.03821  -0.0276   0.1753   1.0000
  10.750   1.1304   0.05010   0.03917  -0.0282   0.1688   1.0000
  11.000   1.1518   0.05169   0.04099  -0.0285   0.1625   1.0000
  11.250   1.1740   0.05313   0.04248  -0.0288   0.1569   1.0000
  11.500   1.1994   0.05453   0.04385  -0.0292   0.1519   1.0000
  11.750   1.2135   0.05663   0.04625  -0.0291   0.1472   1.0000
  12.000   1.2303   0.05844   0.04815  -0.0291   0.1428   1.0000
  12.250   1.2547   0.05989   0.04951  -0.0295   0.1387   1.0000
  12.500   1.2559   0.06282   0.05284  -0.0287   0.1353   1.0000
  12.750   1.2603   0.06551   0.05577  -0.0281   0.1318   1.0000
  13.000   1.2715   0.06760   0.05793  -0.0279   0.1285   1.0000
  13.250   1.2852   0.06970   0.06004  -0.0278   0.1254   1.0000
  13.500   1.2702   0.07398   0.06474  -0.0270   0.1232   1.0000
  13.750   1.2557   0.07841   0.06950  -0.0266   0.1210   1.0000
  14.000   1.2436   0.08275   0.07408  -0.0266   0.1187   1.0000
  14.250   1.2403   0.08630   0.07778  -0.0268   0.1165   1.0000
  14.500   1.2566   0.08796   0.07937  -0.0269   0.1139   1.0000
  14.750   1.2147   0.09605   0.08789  -0.0285   0.1131   1.0000
  15.000   1.1580   0.10748   0.09973  -0.0330   0.1128   1.0000
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