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USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 32 AIRFOIL (usa32-il)
Reynolds number: 100,000
Max Cl/Cd: 41.03 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa32-il-100000-n5.txt
Download as CSV file: xf-usa32-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 32 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0890   0.10765   0.10244  -0.1083   0.8876   0.0673
  -9.000   0.0850   0.10577   0.10057  -0.1140   0.8841   0.0699
  -8.750   0.0656   0.10533   0.10021  -0.1106   0.8723   0.0701
  -8.500   0.0884   0.10069   0.09556  -0.1114   0.8700   0.0709
  -8.250   0.1159   0.09700   0.09184  -0.1124   0.8681   0.0732
  -8.000   0.1124   0.09563   0.09051  -0.1100   0.8590   0.0754
  -7.500   0.0694   0.09424   0.08922  -0.1086   0.8376   0.0805
  -7.000   0.1059   0.08648   0.08144  -0.1101   0.8316   0.0828
  -6.750   0.0934   0.08543   0.08045  -0.1054   0.8185   0.0834
  -6.500   0.1081   0.08231   0.07730  -0.1068   0.8145   0.0850
  -6.000   0.0643   0.07415   0.06903  -0.1055   0.7851   0.0612
  -5.750   0.0784   0.07094   0.06577  -0.1060   0.7807   0.0615
  -5.000   0.0820   0.06061   0.05519  -0.1033   0.7519   0.0528
  -4.750   0.0993   0.05744   0.05191  -0.1038   0.7476   0.0522
  -4.500   0.1028   0.05502   0.04940  -0.1021   0.7379   0.0517
  -4.250   0.1179   0.05031   0.04446  -0.1031   0.7325   0.0518
  -4.000   0.1351   0.04242   0.03602  -0.1055   0.7295   0.0516
  -3.750   0.1354   0.03855   0.03162  -0.1029   0.7191   0.0510
  -3.500   0.1572   0.03501   0.02742  -0.1025   0.7153   0.0509
  -3.250   0.1763   0.03306   0.02500  -0.1011   0.7097   0.0510
  -3.000   0.1947   0.03174   0.02329  -0.0994   0.7030   0.0513
  -2.750   0.2247   0.03020   0.02128  -0.0993   0.6994   0.0525
  -2.500   0.2582   0.02877   0.01951  -0.0999   0.6964   0.0536
  -2.250   0.2739   0.02836   0.01899  -0.0977   0.6884   0.0542
  -2.000   0.3061   0.02735   0.01779  -0.0980   0.6842   0.0547
  -1.750   0.3442   0.02624   0.01652  -0.0993   0.6811   0.0556
  -1.500   0.3652   0.02595   0.01613  -0.0979   0.6744   0.0563
  -1.250   0.3954   0.02536   0.01543  -0.0980   0.6691   0.0573
  -1.000   0.4342   0.02460   0.01452  -0.0995   0.6652   0.0589
  -0.750   0.4637   0.02427   0.01406  -0.0995   0.6598   0.0613
  -0.500   0.4890   0.02402   0.01378  -0.0990   0.6533   0.0637
  -0.250   0.5283   0.02350   0.01314  -0.1008   0.6487   0.0663
   0.000   0.5667   0.02313   0.01261  -0.1025   0.6437   0.0694
   0.250   0.5891   0.02312   0.01259  -0.1015   0.6368   0.0733
   0.500   0.6355   0.02263   0.01209  -0.1050   0.6313   0.0890
   0.750   0.6870   0.02241   0.01220  -0.1097   0.6264   0.2088
   1.000   0.6947   0.02290   0.01269  -0.1058   0.6189   0.2298
   1.250   0.7203   0.02308   0.01277  -0.1052   0.6130   0.2483
   1.500   0.7547   0.02316   0.01271  -0.1062   0.6082   0.2641
   1.750   0.7582   0.02372   0.01326  -0.1018   0.6005   0.2746
   2.000   0.7805   0.02395   0.01346  -0.1006   0.5942   0.2858
   2.250   0.8108   0.02408   0.01348  -0.1010   0.5889   0.3004
   2.500   0.8132   0.02464   0.01410  -0.0965   0.5810   0.3070
   2.750   0.8452   0.02475   0.01406  -0.0974   0.5747   0.3144
   3.000   0.8772   0.02489   0.01416  -0.0985   0.5688   0.3192
   3.250   0.8892   0.02536   0.01466  -0.0961   0.5609   0.3230
   3.500   0.9236   0.02541   0.01460  -0.0975   0.5549   0.3289
   3.750   0.9369   0.02584   0.01503  -0.0953   0.5475   0.3331
   4.000   0.9538   0.02616   0.01536  -0.0936   0.5401   0.3375
   4.250   0.9845   0.02616   0.01527  -0.0943   0.5347   0.3454
   4.500   0.9843   0.02689   0.01607  -0.0898   0.5260   0.3499
   4.750   1.0067   0.02703   0.01620  -0.0891   0.5201   0.3562
   5.000   1.0196   0.02748   0.01663  -0.0869   0.5135   0.3630
   5.250   1.0311   0.02793   0.01713  -0.0845   0.5064   0.3684
   5.500   1.0557   0.02797   0.01708  -0.0841   0.5013   0.3765
   5.750   1.0598   0.02871   0.01789  -0.0807   0.4936   0.3826
   6.000   1.0764   0.02901   0.01816  -0.0791   0.4876   0.3913
   6.250   1.0972   0.02916   0.01829  -0.0781   0.4825   0.4010
   6.500   1.1039   0.02994   0.01912  -0.0753   0.4757   0.4093
   6.750   1.1233   0.03019   0.01937  -0.0743   0.4707   0.4211
   7.000   1.1489   0.03024   0.01940  -0.0742   0.4666   0.4352
   7.250   1.1537   0.03120   0.02048  -0.0714   0.4602   0.4478
   7.750   1.3027   0.03175   0.02189  -0.0921   0.4489   1.0000
   8.000   1.3067   0.03280   0.02300  -0.0891   0.4432   1.0000
   8.250   1.3212   0.03341   0.02361  -0.0874   0.4384   1.0000
   8.500   1.3450   0.03362   0.02374  -0.0870   0.4346   1.0000
   8.750   1.3524   0.03458   0.02474  -0.0846   0.4295   1.0000
   9.000   1.3578   0.03565   0.02586  -0.0819   0.4241   1.0000
   9.250   1.3752   0.03609   0.02628  -0.0807   0.4191   1.0000
   9.500   1.3941   0.03651   0.02665  -0.0798   0.4144   1.0000
   9.750   1.3908   0.03810   0.02836  -0.0763   0.4091   1.0000
  10.000   1.4008   0.03901   0.02930  -0.0744   0.4042   1.0000
  10.250   1.4232   0.03924   0.02950  -0.0739   0.4001   1.0000
  10.500   1.4277   0.04049   0.03082  -0.0715   0.3953   1.0000
  10.750   1.4219   0.04236   0.03281  -0.0682   0.3896   1.0000
  11.000   1.4341   0.04315   0.03361  -0.0668   0.3847   1.0000
  11.250   1.4608   0.04313   0.03355  -0.0667   0.3812   1.0000
  11.500   1.4468   0.04571   0.03632  -0.0630   0.3762   1.0000
  11.750   1.4399   0.04799   0.03874  -0.0602   0.3714   1.0000
  12.000   1.4507   0.04901   0.03980  -0.0589   0.3672   1.0000
  12.250   1.4763   0.04893   0.03969  -0.0587   0.3638   1.0000
  12.500   1.4545   0.05251   0.04347  -0.0552   0.3585   1.0000
  12.750   1.4371   0.05599   0.04710  -0.0523   0.3525   1.0000
  13.000   1.4524   0.05664   0.04779  -0.0515   0.3484   1.0000
  13.250   1.4853   0.05575   0.04687  -0.0516   0.3452   1.0000
  13.500   1.4097   0.06524   0.05670  -0.0469   0.3363   1.0000
  13.750   1.4190   0.06652   0.05804  -0.0460   0.3316   1.0000
  14.000   1.4559   0.06480   0.05628  -0.0459   0.3283   1.0000
  14.250   1.3567   0.07863   0.07045  -0.0430   0.3161   1.0000
  14.500   1.3967   0.07608   0.06786  -0.0426   0.3127   1.0000
  14.750   1.3118   0.08958   0.08159  -0.0417   0.2989   1.0000
  15.000   1.3528   0.08656   0.07858  -0.0410   0.2960   1.0000
  15.500   1.3270   0.09518   0.08736  -0.0403   0.2792   1.0000
  16.000   1.3115   0.10278   0.09510  -0.0402   0.2628   1.0000
  16.500   1.3017   0.10979   0.10223  -0.0404   0.2472   1.0000
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