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USA 41 AIRFOIL (usa41-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 41 AIRFOIL (usa41-il)
Reynolds number: 100,000
Max Cl/Cd: 60.9 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa41-il-100000-n5.txt
Download as CSV file: xf-usa41-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 41 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3436   0.10532   0.10043  -0.0295   1.0000   0.0388
  -8.250  -0.3447   0.10306   0.09825  -0.0301   1.0000   0.0389
  -8.000  -0.3462   0.10074   0.09601  -0.0302   1.0000   0.0389
  -7.750  -0.3463   0.09810   0.09345  -0.0312   1.0000   0.0390
  -7.500  -0.3441   0.09492   0.09037  -0.0320   1.0000   0.0391
  -7.250  -0.3291   0.08995   0.08532  -0.0255   1.0000   0.0435
  -7.000  -0.3307   0.08790   0.08336  -0.0249   1.0000   0.0458
  -6.750  -0.3319   0.08571   0.08124  -0.0255   1.0000   0.0479
  -6.500  -0.3335   0.08416   0.07979  -0.0319   1.0000   0.0505
  -6.250  -0.3269   0.08142   0.07706  -0.0370   1.0000   0.0510
  -6.000  -0.3301   0.07748   0.07321  -0.0328   1.0000   0.0520
  -5.750  -0.3290   0.07503   0.07081  -0.0293   1.0000   0.0534
  -5.500  -0.3241   0.07255   0.06835  -0.0288   0.9999   0.0550
  -5.250  -0.2666   0.06234   0.05785  -0.0478   0.9919   0.0385
  -5.000  -0.2302   0.06019   0.05563  -0.0558   0.9852   0.0649
  -4.500  -0.1484   0.04361   0.03840  -0.0718   0.9729   0.0385
  -4.250  -0.1144   0.03981   0.03441  -0.0765   0.9670   0.0416
  -4.000  -0.0781   0.03575   0.03003  -0.0808   0.9602   0.0437
  -3.750  -0.0366   0.02992   0.02352  -0.0858   0.9549   0.0437
  -3.500  -0.0003   0.02674   0.01975  -0.0886   0.9485   0.0474
  -3.250   0.0363   0.02383   0.01616  -0.0908   0.9424   0.0484
  -3.000   0.0756   0.02170   0.01344  -0.0931   0.9378   0.0493
  -2.750   0.1082   0.02044   0.01177  -0.0939   0.9295   0.0513
  -2.500   0.1459   0.01906   0.01022  -0.0959   0.9242   0.0539
  -2.250   0.1774   0.01812   0.00910  -0.0964   0.9149   0.0545
  -2.000   0.2132   0.01728   0.00810  -0.0977   0.9076   0.0554
  -1.750   0.2457   0.01662   0.00735  -0.0983   0.8978   0.0567
  -1.500   0.2773   0.01608   0.00673  -0.0988   0.8872   0.0586
  -1.250   0.3096   0.01562   0.00616  -0.0993   0.8764   0.0612
  -1.000   0.3419   0.01521   0.00568  -0.0997   0.8649   0.0652
  -0.750   0.3724   0.01482   0.00530  -0.0999   0.8520   0.0748
  -0.500   0.4011   0.01443   0.00517  -0.0998   0.8373   0.1282
  -0.250   0.4298   0.01438   0.00510  -0.0995   0.8212   0.1918
   0.000   0.4586   0.01422   0.00492  -0.0994   0.8044   0.2239
   0.250   0.4876   0.01407   0.00470  -0.0993   0.7870   0.2404
   0.500   0.5168   0.01385   0.00451  -0.0992   0.7692   0.2716
   0.750   0.5442   0.01290   0.00451  -0.0991   0.7517   0.5893
   1.250   0.6103   0.01234   0.00424  -0.1003   0.7116   1.0000
   1.500   0.6372   0.01249   0.00420  -0.0997   0.6920   1.0000
   1.750   0.6634   0.01266   0.00423  -0.0991   0.6717   1.0000
   2.000   0.6896   0.01285   0.00427  -0.0985   0.6524   1.0000
   2.250   0.7156   0.01307   0.00435  -0.0979   0.6339   1.0000
   2.500   0.7413   0.01330   0.00449  -0.0972   0.6158   1.0000
   2.750   0.7670   0.01355   0.00464  -0.0966   0.5984   1.0000
   3.000   0.7925   0.01381   0.00482  -0.0960   0.5821   1.0000
   3.250   0.8180   0.01409   0.00506  -0.0954   0.5666   1.0000
   3.500   0.8433   0.01438   0.00530  -0.0947   0.5516   1.0000
   3.750   0.8686   0.01469   0.00557  -0.0941   0.5374   1.0000
   4.000   0.8937   0.01500   0.00588  -0.0935   0.5235   1.0000
   4.250   0.9187   0.01533   0.00623  -0.0929   0.5098   1.0000
   4.500   0.9436   0.01567   0.00659  -0.0922   0.4965   1.0000
   4.750   0.9684   0.01602   0.00697  -0.0916   0.4834   1.0000
   5.000   0.9930   0.01639   0.00741  -0.0909   0.4705   1.0000
   5.500   1.0419   0.01712   0.00831  -0.0895   0.4452   1.0000
   5.750   1.0658   0.01750   0.00880  -0.0887   0.4315   1.0000
   6.000   1.0895   0.01789   0.00934  -0.0878   0.4175   1.0000
   6.250   1.1119   0.01827   0.00979  -0.0867   0.3995   1.0000
   6.500   1.1300   0.01860   0.01010  -0.0849   0.3596   1.0000
   6.750   1.1465   0.01917   0.01050  -0.0830   0.3068   1.0000
   7.000   1.1616   0.02008   0.01112  -0.0811   0.2372   1.0000
   7.250   1.1676   0.02224   0.01241  -0.0785   0.1084   1.0000
   7.500   1.1735   0.02467   0.01434  -0.0757   0.0473   1.0000
   7.750   1.1857   0.02626   0.01595  -0.0735   0.0370   1.0000
   8.000   1.1974   0.02776   0.01758  -0.0712   0.0320   1.0000
   8.250   1.2076   0.02927   0.01926  -0.0688   0.0285   1.0000
   8.500   1.2170   0.03074   0.02093  -0.0663   0.0262   1.0000
   8.750   1.2238   0.03233   0.02269  -0.0636   0.0248   1.0000
   9.000   1.2278   0.03398   0.02446  -0.0605   0.0235   1.0000
   9.250   1.2295   0.03585   0.02641  -0.0575   0.0223   1.0000
   9.500   1.2313   0.03815   0.02876  -0.0546   0.0209   1.0000
   9.750   1.2411   0.03984   0.03068  -0.0526   0.0199   1.0000
  10.000   1.2521   0.04189   0.03290  -0.0507   0.0192   1.0000
  10.250   1.2650   0.04420   0.03539  -0.0491   0.0186   1.0000
  10.500   1.2781   0.04675   0.03817  -0.0476   0.0180   1.0000
  10.750   1.2882   0.04945   0.04114  -0.0459   0.0175   1.0000
  11.000   1.2938   0.05220   0.04415  -0.0442   0.0169   1.0000
  11.250   1.2945   0.05497   0.04718  -0.0425   0.0161   1.0000
  11.500   1.2924   0.05792   0.05037  -0.0410   0.0156   1.0000
  11.750   1.2876   0.06111   0.05382  -0.0398   0.0152   1.0000
  12.000   1.2808   0.06469   0.05765  -0.0389   0.0149   1.0000
  12.250   1.2717   0.06862   0.06183  -0.0386   0.0147   1.0000
  12.500   1.2607   0.07304   0.06651  -0.0388   0.0146   1.0000
  12.750   1.2477   0.07792   0.07164  -0.0397   0.0146   1.0000
  13.000   1.2333   0.08328   0.07726  -0.0413   0.0146   1.0000
  13.250   1.2172   0.08920   0.08341  -0.0436   0.0146   1.0000
  13.500   1.2000   0.09567   0.09011  -0.0468   0.0147   1.0000
  13.750   1.1816   0.10284   0.09750  -0.0507   0.0148   1.0000
  14.000   1.1620   0.11077   0.10564  -0.0554   0.0149   1.0000
  14.250   1.1411   0.11978   0.11484  -0.0612   0.0152   1.0000
  14.500   1.1181   0.13032   0.12555  -0.0682   0.0155   1.0000
  14.750   1.0915   0.14349   0.13886  -0.0769   0.0163   1.0000
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