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S2055 (s2055-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S2055 (s2055-il)
Reynolds number: 200,000
Max Cl/Cd: 61.94 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2055-il-200000-n5.txt
Download as CSV file: xf-s2055-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4811   0.08793   0.08435  -0.0269   1.0000   0.0124
  -8.750  -0.4835   0.08379   0.08025  -0.0288   1.0000   0.0123
  -8.500  -0.4895   0.07889   0.07542  -0.0314   1.0000   0.0127
  -8.250  -0.4966   0.07497   0.07156  -0.0333   1.0000   0.0125
  -8.000  -0.5093   0.07092   0.06756  -0.0353   1.0000   0.0123
  -7.750  -0.5168   0.06630   0.06294  -0.0371   1.0000   0.0122
  -7.500  -0.5226   0.06201   0.05860  -0.0379   1.0000   0.0120
  -7.250  -0.5269   0.05772   0.05424  -0.0378   1.0000   0.0118
  -7.000  -0.5309   0.05305   0.04944  -0.0371   1.0000   0.0117
  -6.750  -0.5323   0.04851   0.04472  -0.0358   1.0000   0.0115
  -6.500  -0.5311   0.04408   0.04006  -0.0342   1.0000   0.0113
  -6.250  -0.5279   0.03950   0.03518  -0.0322   1.0000   0.0112
  -6.000  -0.5114   0.03376   0.02893  -0.0325   0.9974   0.0111
  -5.750  -0.4856   0.02845   0.02294  -0.0337   0.9937   0.0110
  -5.500  -0.4590   0.02448   0.01831  -0.0341   0.9897   0.0113
  -5.250  -0.4295   0.02166   0.01489  -0.0346   0.9864   0.0118
  -5.000  -0.3980   0.01957   0.01236  -0.0354   0.9838   0.0126
  -4.750  -0.3682   0.01810   0.01062  -0.0360   0.9805   0.0141
  -4.500  -0.3388   0.01718   0.00964  -0.0367   0.9763   0.0163
  -4.250  -0.3073   0.01605   0.00835  -0.0375   0.9730   0.0185
  -4.000  -0.2744   0.01503   0.00719  -0.0386   0.9704   0.0209
  -3.750  -0.2462   0.01437   0.00648  -0.0389   0.9654   0.0267
  -3.500  -0.2154   0.01370   0.00572  -0.0396   0.9611   0.0319
  -3.250  -0.1818   0.01324   0.00522  -0.0410   0.9580   0.0412
  -3.000  -0.1502   0.01268   0.00469  -0.0419   0.9541   0.0588
  -2.750  -0.1212   0.01226   0.00435  -0.0423   0.9485   0.0884
  -2.500  -0.0886   0.01177   0.00403  -0.0436   0.9449   0.1423
  -2.250  -0.0602   0.01089   0.00380  -0.0444   0.9404   0.2964
  -2.000  -0.0374   0.00992   0.00363  -0.0438   0.9336   0.5055
  -1.750  -0.0122   0.00919   0.00363  -0.0429   0.9294   0.6962
  -1.500   0.0107   0.00901   0.00368  -0.0412   0.9220   0.7890
  -1.250   0.0396   0.00894   0.00365  -0.0407   0.9170   0.8460
  -1.000   0.0667   0.00893   0.00365  -0.0398   0.9102   0.8903
  -0.750   0.0996   0.00893   0.00363  -0.0401   0.9043   0.9257
  -0.500   0.1397   0.00891   0.00354  -0.0421   0.8977   0.9488
  -0.250   0.1828   0.00883   0.00339  -0.0449   0.8888   0.9624
   0.000   0.2246   0.00872   0.00320  -0.0475   0.8753   0.9721
   0.250   0.2673   0.00861   0.00301  -0.0503   0.8601   0.9788
   0.500   0.3060   0.00853   0.00286  -0.0524   0.8446   0.9849
   0.750   0.3439   0.00847   0.00274  -0.0545   0.8292   0.9903
   1.000   0.3797   0.00843   0.00265  -0.0561   0.8137   0.9957
   1.250   0.4133   0.00841   0.00259  -0.0574   0.7965   1.0000
   1.500   0.4359   0.00843   0.00256  -0.0562   0.7790   1.0000
   1.750   0.4580   0.00847   0.00255  -0.0550   0.7591   1.0000
   2.000   0.4800   0.00854   0.00256  -0.0537   0.7377   1.0000
   2.250   0.5017   0.00862   0.00261  -0.0524   0.7132   1.0000
   2.500   0.5232   0.00874   0.00265  -0.0510   0.6841   1.0000
   2.750   0.5442   0.00889   0.00270  -0.0495   0.6490   1.0000
   3.000   0.5643   0.00911   0.00277  -0.0478   0.6048   1.0000
   3.250   0.5831   0.00943   0.00290  -0.0459   0.5502   1.0000
   3.500   0.6010   0.00986   0.00306  -0.0439   0.4908   1.0000
   3.750   0.6187   0.01036   0.00328  -0.0420   0.4299   1.0000
   4.000   0.6368   0.01092   0.00356  -0.0403   0.3703   1.0000
   4.250   0.6562   0.01145   0.00386  -0.0389   0.3201   1.0000
   4.500   0.6774   0.01190   0.00420  -0.0378   0.2836   1.0000
   4.750   0.6993   0.01232   0.00453  -0.0369   0.2542   1.0000
   5.000   0.7217   0.01274   0.00487  -0.0360   0.2271   1.0000
   5.250   0.7444   0.01314   0.00524  -0.0352   0.2028   1.0000
   5.500   0.7665   0.01364   0.00563  -0.0344   0.1712   1.0000
   5.750   0.7880   0.01423   0.00605  -0.0335   0.1303   1.0000
   6.000   0.8085   0.01497   0.00662  -0.0325   0.0895   1.0000
   6.250   0.8293   0.01572   0.00725  -0.0315   0.0640   1.0000
   6.500   0.8508   0.01640   0.00791  -0.0306   0.0500   1.0000
   6.750   0.8719   0.01715   0.00867  -0.0296   0.0406   1.0000
   7.000   0.8934   0.01784   0.00947  -0.0287   0.0346   1.0000
   7.250   0.9123   0.01885   0.01053  -0.0273   0.0303   1.0000
   7.500   0.9328   0.01964   0.01147  -0.0262   0.0277   1.0000
   7.750   0.9534   0.02042   0.01235  -0.0252   0.0247   1.0000
   8.000   0.9722   0.02141   0.01342  -0.0239   0.0225   1.0000
   8.250   0.9870   0.02305   0.01521  -0.0221   0.0207   1.0000
   8.500   1.0071   0.02396   0.01631  -0.0211   0.0193   1.0000
   8.750   1.0266   0.02486   0.01738  -0.0200   0.0170   1.0000
   9.000   1.0441   0.02604   0.01869  -0.0187   0.0155   1.0000
   9.250   1.0582   0.02760   0.02035  -0.0172   0.0139   1.0000
   9.500   1.0742   0.02899   0.02197  -0.0158   0.0125   1.0000
   9.750   1.0888   0.03055   0.02378  -0.0142   0.0111   1.0000
  10.000   1.1008   0.03233   0.02580  -0.0124   0.0104   1.0000
  10.250   1.1108   0.03398   0.02768  -0.0105   0.0096   1.0000
  10.500   1.1171   0.03580   0.02970  -0.0083   0.0092   1.0000
  10.750   1.1172   0.03805   0.03215  -0.0054   0.0088   1.0000
  11.000   1.1097   0.04123   0.03562  -0.0023   0.0085   1.0000
  11.250   1.1016   0.04424   0.03894   0.0004   0.0083   1.0000
  11.500   1.0924   0.04734   0.04233   0.0025   0.0082   1.0000
  11.750   1.0800   0.05092   0.04619   0.0038   0.0081   1.0000
  12.000   1.0646   0.05514   0.05068   0.0040   0.0080   1.0000
  12.250   1.0489   0.05984   0.05561   0.0030   0.0081   1.0000
  12.500   1.0314   0.06547   0.06145   0.0005   0.0080   1.0000
  12.750   1.0128   0.07216   0.06833  -0.0034   0.0081   1.0000
  13.000   0.9943   0.07992   0.07627  -0.0088   0.0082   1.0000
  13.250   0.9748   0.08907   0.08556  -0.0153   0.0083   1.0000
  13.500   0.9546   0.09900   0.09560  -0.0219   0.0084   1.0000
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