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S2055 (s2055-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S2055 (s2055-il)
Reynolds number: 50,000
Max Cl/Cd: 35.12 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2055-il-50000.txt
Download as CSV file: xf-s2055-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2055                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4736   0.10208   0.09526  -0.0125   1.0000   0.2395
  -8.250  -0.4870   0.10061   0.09392  -0.0133   1.0000   0.2506
  -8.000  -0.4804   0.09709   0.09045  -0.0123   1.0000   0.2643
  -7.750  -0.4610   0.09249   0.08581  -0.0100   1.0000   0.2854
  -7.500  -0.4610   0.08988   0.08328  -0.0088   1.0000   0.3035
  -7.250  -0.4737   0.08806   0.08160  -0.0076   1.0000   0.3206
  -7.000  -0.4614   0.08452   0.07810  -0.0050   1.0000   0.3475
  -6.750  -0.4503   0.08102   0.07463  -0.0027   1.0000   0.3714
  -6.500  -0.4491   0.07828   0.07198   0.0001   1.0000   0.3969
  -6.250  -0.4427   0.07543   0.06919   0.0030   1.0000   0.4260
  -6.000  -0.4378   0.07281   0.06663   0.0065   1.0000   0.4591
  -5.000  -0.4578   0.04611   0.03807  -0.0310   1.0000   0.1380
  -4.750  -0.4387   0.04174   0.03314  -0.0303   1.0000   0.1238
  -4.500  -0.4200   0.03808   0.02925  -0.0292   1.0000   0.1189
  -4.250  -0.3990   0.03484   0.02544  -0.0281   1.0000   0.1157
  -4.000  -0.3775   0.03238   0.02251  -0.0269   1.0000   0.1207
  -3.750  -0.3536   0.02999   0.01953  -0.0256   1.0000   0.1235
  -3.500  -0.3293   0.02761   0.01687  -0.0245   1.0000   0.1275
  -3.250  -0.3056   0.02582   0.01490  -0.0233   1.0000   0.1418
  -3.000  -0.2804   0.02404   0.01302  -0.0220   1.0000   0.1586
  -2.750  -0.1510   0.01755   0.00993  -0.0319   1.0000   1.0000
  -2.500  -0.1446   0.01737   0.00932  -0.0288   1.0000   1.0000
  -2.250  -0.1372   0.01723   0.00883  -0.0258   1.0000   1.0000
  -2.000  -0.1284   0.01715   0.00840  -0.0230   1.0000   1.0000
  -1.750  -0.1181   0.01711   0.00806  -0.0204   1.0000   1.0000
  -1.500  -0.1057   0.01711   0.00779  -0.0182   1.0000   1.0000
  -1.250  -0.0916   0.01716   0.00757  -0.0163   1.0000   1.0000
  -1.000  -0.0761   0.01724   0.00742  -0.0147   1.0000   1.0000
  -0.750  -0.0594   0.01736   0.00731  -0.0132   1.0000   1.0000
  -0.500  -0.0421   0.01751   0.00724  -0.0120   1.0000   1.0000
  -0.250  -0.0241   0.01769   0.00725  -0.0109   1.0000   1.0000
   0.000  -0.0058   0.01791   0.00731  -0.0099   1.0000   1.0000
   0.250   0.0128   0.01815   0.00742  -0.0090   1.0000   1.0000
   0.500   0.0317   0.01843   0.00756  -0.0081   1.0000   1.0000
   0.750   0.0506   0.01874   0.00777  -0.0074   1.0000   1.0000
   1.000   0.0695   0.01909   0.00805  -0.0067   1.0000   1.0000
   1.250   0.0883   0.01947   0.00837  -0.0061   1.0000   1.0000
   1.500   0.1070   0.01990   0.00876  -0.0055   1.0000   1.0000
   1.750   0.1256   0.02037   0.00920  -0.0050   1.0000   1.0000
   2.000   0.1439   0.02088   0.00971  -0.0046   1.0000   1.0000
   2.250   0.1618   0.02146   0.01029  -0.0042   1.0000   1.0000
   2.500   0.1793   0.02210   0.01095  -0.0039   1.0000   1.0000
   2.750   0.1963   0.02281   0.01171  -0.0037   1.0000   1.0000
   3.000   0.2264   0.02390   0.01290  -0.0062   0.9938   1.0000
   3.250   0.3005   0.02554   0.01477  -0.0166   0.9619   1.0000
   3.500   0.3742   0.02664   0.01618  -0.0258   0.9295   1.0000
   3.750   0.4362   0.02706   0.01691  -0.0320   0.8944   1.0000
   4.000   0.5120   0.02680   0.01709  -0.0392   0.8588   1.0000
   4.250   0.5854   0.02570   0.01654  -0.0444   0.8188   1.0000
   4.500   0.6478   0.02410   0.01539  -0.0462   0.7731   1.0000
   4.750   0.6963   0.02255   0.01418  -0.0450   0.7163   1.0000
   5.000   0.7310   0.02161   0.01325  -0.0420   0.6482   1.0000
   5.250   0.7552   0.02155   0.01297  -0.0385   0.5758   1.0000
   5.500   0.7757   0.02209   0.01316  -0.0354   0.5067   1.0000
   5.750   0.7937   0.02304   0.01381  -0.0325   0.4416   1.0000
   6.000   0.8099   0.02430   0.01477  -0.0297   0.3769   1.0000
   6.250   0.8247   0.02591   0.01600  -0.0269   0.3084   1.0000
   6.500   0.8409   0.02798   0.01756  -0.0245   0.2433   1.0000
   6.750   0.8595   0.03018   0.01967  -0.0225   0.1966   1.0000
   7.000   0.8790   0.03219   0.02160  -0.0209   0.1646   1.0000
   7.250   0.9019   0.03481   0.02434  -0.0197   0.1446   1.0000
   7.500   0.9213   0.03729   0.02710  -0.0182   0.1289   1.0000
   7.750   0.9449   0.04066   0.03049  -0.0173   0.1203   1.0000
   8.000   0.9569   0.04429   0.03496  -0.0149   0.1158   1.0000
   8.250   0.9756   0.04740   0.03799  -0.0141   0.1071   1.0000
   8.500   0.9804   0.05150   0.04283  -0.0115   0.1055   1.0000
   8.750   0.9837   0.05610   0.04796  -0.0094   0.1054   1.0000
   9.000   0.9838   0.06095   0.05324  -0.0075   0.1059   1.0000
   9.250   0.9843   0.06607   0.05864  -0.0061   0.1068   1.0000
   9.500   0.9472   0.07156   0.06480  -0.0041   0.1115   1.0000
   9.750   0.9203   0.07701   0.07044  -0.0035   0.1146   1.0000
  10.000   0.9001   0.08223   0.07573  -0.0036   0.1171   1.0000
  10.250   0.8950   0.08781   0.08133  -0.0041   0.1195   1.0000
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