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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 100,000
Max Cl/Cd: 56.2 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4083-il-100000-n5.txt
Download as CSV file: xf-s4083-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4083 (8%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3920   0.10386   0.09900  -0.0229   1.0000   0.0426
  -8.000  -0.3924   0.10105   0.09627  -0.0239   1.0000   0.0427
  -7.750  -0.3927   0.09806   0.09335  -0.0251   1.0000   0.0427
  -7.500  -0.3891   0.09438   0.08976  -0.0274   1.0000   0.0428
  -7.250  -0.3835   0.08949   0.08489  -0.0230   1.0000   0.0439
  -7.000  -0.3780   0.08630   0.08172  -0.0226   1.0000   0.0445
  -6.750  -0.3724   0.08338   0.07885  -0.0222   1.0000   0.0456
  -6.500  -0.3669   0.08058   0.07610  -0.0225   1.0000   0.0477
  -6.250  -0.3614   0.07743   0.07300  -0.0244   1.0000   0.0502
  -6.000  -0.3533   0.07373   0.06934  -0.0285   1.0000   0.0527
  -5.750  -0.3314   0.06819   0.06358  -0.0423   1.0000   0.0554
  -5.500  -0.3229   0.06337   0.05880  -0.0432   1.0000   0.0562
  -5.000  -0.2937   0.05209   0.04738  -0.0448   1.0000   0.0295
  -4.750  -0.2772   0.04805   0.04323  -0.0465   1.0000   0.0282
  -4.500  -0.2563   0.04336   0.03833  -0.0490   1.0000   0.0268
  -4.250  -0.2323   0.03840   0.03302  -0.0513   1.0000   0.0254
  -4.000  -0.2061   0.03350   0.02761  -0.0532   1.0000   0.0241
  -3.750  -0.1773   0.02921   0.02262  -0.0544   0.9996   0.0231
  -3.500  -0.1348   0.02586   0.01862  -0.0579   0.9934   0.0228
  -3.250  -0.0940   0.02330   0.01551  -0.0607   0.9860   0.0229
  -3.000  -0.0554   0.02127   0.01310  -0.0628   0.9766   0.0234
  -2.750  -0.0180   0.01965   0.01121  -0.0645   0.9658   0.0246
  -2.500   0.0188   0.01851   0.00989  -0.0661   0.9532   0.0281
  -2.250   0.0550   0.01737   0.00856  -0.0674   0.9392   0.0316
  -2.000   0.0908   0.01618   0.00733  -0.0687   0.9238   0.0359
  -1.750   0.1293   0.01521   0.00627  -0.0705   0.9068   0.0492
  -1.500   0.1679   0.01403   0.00549  -0.0726   0.8862   0.1340
  -1.250   0.2083   0.01280   0.00509  -0.0753   0.8630   0.3873
  -1.000   0.2449   0.01180   0.00486  -0.0764   0.8345   0.6654
  -0.750   0.3009   0.01105   0.00433  -0.0809   0.7994   1.0000
  -0.500   0.3388   0.01116   0.00400  -0.0825   0.7613   1.0000
  -0.250   0.3717   0.01134   0.00380  -0.0832   0.7255   1.0000
   0.000   0.4018   0.01155   0.00367  -0.0833   0.6939   1.0000
   0.500   0.4580   0.01201   0.00357  -0.0829   0.6410   1.0000
   0.750   0.4851   0.01225   0.00358  -0.0826   0.6193   1.0000
   1.000   0.5118   0.01249   0.00362  -0.0822   0.5996   1.0000
   1.250   0.5383   0.01274   0.00368  -0.0817   0.5821   1.0000
   1.500   0.5646   0.01299   0.00376  -0.0813   0.5660   1.0000
   1.750   0.5908   0.01325   0.00388  -0.0808   0.5511   1.0000
   2.000   0.6169   0.01350   0.00403  -0.0804   0.5372   1.0000
   2.250   0.6429   0.01376   0.00419  -0.0799   0.5239   1.0000
   2.500   0.6689   0.01402   0.00437  -0.0794   0.5114   1.0000
   2.750   0.6948   0.01428   0.00457  -0.0790   0.4994   1.0000
   3.000   0.7206   0.01456   0.00483  -0.0785   0.4881   1.0000
   3.250   0.7463   0.01485   0.00505  -0.0780   0.4772   1.0000
   3.500   0.7719   0.01515   0.00530  -0.0775   0.4663   1.0000
   3.750   0.7974   0.01543   0.00559  -0.0770   0.4550   1.0000
   4.000   0.8228   0.01572   0.00589  -0.0764   0.4442   1.0000
   4.250   0.8481   0.01604   0.00623  -0.0759   0.4342   1.0000
   4.500   0.8733   0.01635   0.00655  -0.0753   0.4239   1.0000
   4.750   0.8984   0.01666   0.00693  -0.0747   0.4133   1.0000
   5.000   0.9233   0.01699   0.00730  -0.0742   0.4029   1.0000
   5.250   0.9480   0.01733   0.00771  -0.0735   0.3928   1.0000
   5.500   0.9725   0.01766   0.00811  -0.0728   0.3817   1.0000
   5.750   0.9968   0.01799   0.00855  -0.0721   0.3701   1.0000
   6.000   1.0208   0.01834   0.00899  -0.0714   0.3584   1.0000
   6.250   1.0446   0.01870   0.00948  -0.0706   0.3467   1.0000
   6.500   1.0681   0.01907   0.00995  -0.0698   0.3344   1.0000
   6.750   1.0911   0.01944   0.01043  -0.0689   0.3212   1.0000
   7.000   1.1138   0.01982   0.01094  -0.0680   0.3066   1.0000
   7.250   1.1361   0.02022   0.01148  -0.0670   0.2913   1.0000
   7.500   1.1579   0.02066   0.01209  -0.0660   0.2752   1.0000
   7.750   1.1790   0.02114   0.01269  -0.0648   0.2582   1.0000
   8.000   1.1992   0.02169   0.01333  -0.0636   0.2392   1.0000
   8.250   1.2188   0.02230   0.01405  -0.0623   0.2171   1.0000
   8.500   1.2366   0.02305   0.01484  -0.0609   0.1910   1.0000
   8.750   1.2514   0.02407   0.01575  -0.0592   0.1573   1.0000
   9.000   1.2634   0.02544   0.01696  -0.0575   0.1171   1.0000
   9.250   1.2724   0.02716   0.01842  -0.0554   0.0771   1.0000
   9.500   1.2798   0.02899   0.02009  -0.0531   0.0496   1.0000
   9.750   1.2846   0.03095   0.02202  -0.0504   0.0332   1.0000
  10.000   1.2864   0.03303   0.02414  -0.0475   0.0261   1.0000
  10.250   1.2872   0.03488   0.02618  -0.0443   0.0226   1.0000
  10.500   1.2835   0.03694   0.02838  -0.0410   0.0206   1.0000
  10.750   1.2763   0.03932   0.03091  -0.0379   0.0195   1.0000
  11.000   1.2711   0.04173   0.03350  -0.0356   0.0188   1.0000
  11.250   1.2649   0.04450   0.03649  -0.0341   0.0181   1.0000
  11.500   1.2584   0.04764   0.03983  -0.0333   0.0176   1.0000
  11.750   1.2516   0.05117   0.04354  -0.0332   0.0171   1.0000
  12.000   1.2451   0.05496   0.04752  -0.0337   0.0167   1.0000
  12.250   1.2388   0.05899   0.05172  -0.0344   0.0164   1.0000
  12.500   1.2330   0.06311   0.05601  -0.0353   0.0160   1.0000
  12.750   1.2278   0.06729   0.06040  -0.0364   0.0157   1.0000
  13.000   1.2210   0.07183   0.06510  -0.0379   0.0151   1.0000
  13.250   1.2149   0.07638   0.06980  -0.0393   0.0148   1.0000
  13.500   1.2090   0.08095   0.07452  -0.0408   0.0146   1.0000
  13.750   1.2008   0.08604   0.07974  -0.0429   0.0141   1.0000
  14.000   1.1932   0.09113   0.08497  -0.0449   0.0139   1.0000
  14.250   1.1851   0.09643   0.09040  -0.0472   0.0136   1.0000
  14.500   1.1769   0.10192   0.09603  -0.0495   0.0134   1.0000
  14.750   1.1685   0.10766   0.10192  -0.0520   0.0132   1.0000
  15.000   1.1586   0.11393   0.10833  -0.0551   0.0130   1.0000
  15.250   1.1488   0.12056   0.11514  -0.0587   0.0129   1.0000
  15.500   1.1389   0.12746   0.12220  -0.0625   0.0129   1.0000
  15.750   1.1281   0.13484   0.12974  -0.0668   0.0129   1.0000
  16.000   1.1171   0.14259   0.13764  -0.0713   0.0130   1.0000
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