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S2055 (s2055-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S2055 (s2055-il)
Reynolds number: 50,000
Max Cl/Cd: 35.22 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2055-il-50000-n5.txt
Download as CSV file: xf-s2055-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4783   0.09488   0.08788  -0.0265   1.0000   0.0490
  -8.500  -0.4807   0.09068   0.08377  -0.0284   1.0000   0.0471
  -8.250  -0.4867   0.08625   0.07944  -0.0310   1.0000   0.0454
  -7.750  -0.5065   0.07595   0.06916  -0.0384   1.0000   0.0412
  -7.500  -0.5067   0.07225   0.06547  -0.0383   1.0000   0.0407
  -7.250  -0.5072   0.06854   0.06173  -0.0383   1.0000   0.0403
  -7.000  -0.5078   0.06462   0.05775  -0.0381   1.0000   0.0398
  -6.750  -0.5068   0.06074   0.05375  -0.0378   1.0000   0.0394
  -6.500  -0.5040   0.05688   0.04971  -0.0372   1.0000   0.0391
  -6.250  -0.4992   0.05303   0.04563  -0.0364   1.0000   0.0388
  -6.000  -0.4923   0.04919   0.04141  -0.0354   1.0000   0.0387
  -5.750  -0.4827   0.04556   0.03742  -0.0342   1.0000   0.0387
  -5.500  -0.4706   0.04208   0.03347  -0.0329   1.0000   0.0397
  -5.250  -0.4555   0.03899   0.02970  -0.0314   1.0000   0.0415
  -5.000  -0.4409   0.03635   0.02694  -0.0303   1.0000   0.0445
  -4.750  -0.4228   0.03398   0.02424  -0.0291   1.0000   0.0468
  -4.500  -0.4025   0.03149   0.02129  -0.0277   1.0000   0.0485
  -4.250  -0.3804   0.02920   0.01854  -0.0263   1.0000   0.0512
  -4.000  -0.3590   0.02750   0.01656  -0.0251   1.0000   0.0577
  -3.750  -0.3367   0.02608   0.01488  -0.0238   1.0000   0.0652
  -3.500  -0.3140   0.02452   0.01318  -0.0224   1.0000   0.0708
  -3.250  -0.2913   0.02334   0.01171  -0.0210   1.0000   0.0799
  -3.000  -0.2693   0.02231   0.01071  -0.0201   1.0000   0.1003
  -2.750  -0.2481   0.02122   0.00966  -0.0190   1.0000   0.1318
  -2.500  -0.2278   0.01984   0.00884  -0.0183   1.0000   0.2174
  -2.250  -0.2157   0.01764   0.00845  -0.0156   1.0000   0.5401
  -2.000  -0.1278   0.01716   0.00840  -0.0228   1.0000   1.0000
  -1.750  -0.1176   0.01713   0.00807  -0.0202   1.0000   1.0000
  -1.500  -0.1054   0.01713   0.00779  -0.0180   1.0000   1.0000
  -1.250  -0.0914   0.01717   0.00758  -0.0161   1.0000   1.0000
  -1.000  -0.0759   0.01726   0.00742  -0.0144   1.0000   1.0000
  -0.750  -0.0594   0.01737   0.00732  -0.0130   1.0000   1.0000
  -0.500  -0.0421   0.01752   0.00724  -0.0117   1.0000   1.0000
  -0.250  -0.0242   0.01771   0.00725  -0.0106   1.0000   1.0000
   0.000   0.0028   0.01800   0.00737  -0.0113   0.9963   1.0000
   0.250   0.0407   0.01840   0.00762  -0.0141   0.9875   1.0000
   0.500   0.0789   0.01880   0.00788  -0.0168   0.9785   1.0000
   0.750   0.1190   0.01923   0.00821  -0.0199   0.9695   1.0000
   1.000   0.1563   0.01956   0.00848  -0.0224   0.9583   1.0000
   1.250   0.1942   0.01986   0.00876  -0.0248   0.9463   1.0000
   1.500   0.2332   0.02011   0.00901  -0.0274   0.9332   1.0000
   1.750   0.2733   0.02030   0.00924  -0.0299   0.9190   1.0000
   2.000   0.3155   0.02039   0.00941  -0.0326   0.9036   1.0000
   2.250   0.3605   0.02035   0.00947  -0.0356   0.8878   1.0000
   2.500   0.3965   0.02029   0.00952  -0.0368   0.8686   1.0000
   2.750   0.4352   0.02013   0.00954  -0.0382   0.8503   1.0000
   3.000   0.4723   0.01994   0.00949  -0.0391   0.8312   1.0000
   3.250   0.5040   0.01979   0.00950  -0.0390   0.8089   1.0000
   3.500   0.5349   0.01964   0.00951  -0.0387   0.7847   1.0000
   3.750   0.5648   0.01949   0.00957  -0.0380   0.7570   1.0000
   4.000   0.5940   0.01935   0.00959  -0.0372   0.7249   1.0000
   4.250   0.6210   0.01929   0.00965  -0.0359   0.6855   1.0000
   4.500   0.6479   0.01926   0.00969  -0.0346   0.6381   1.0000
   4.750   0.6732   0.01940   0.00985  -0.0329   0.5798   1.0000
   5.000   0.6966   0.01978   0.01003  -0.0311   0.5161   1.0000
   5.250   0.7167   0.02046   0.01045  -0.0292   0.4546   1.0000
   5.500   0.7351   0.02131   0.01106  -0.0273   0.3992   1.0000
   5.750   0.7526   0.02224   0.01177  -0.0256   0.3493   1.0000
   6.000   0.7699   0.02318   0.01259  -0.0239   0.3017   1.0000
   6.250   0.7871   0.02417   0.01348  -0.0224   0.2571   1.0000
   6.500   0.8036   0.02527   0.01457  -0.0209   0.2121   1.0000
   6.750   0.8205   0.02654   0.01574  -0.0194   0.1675   1.0000
   7.000   0.8370   0.02799   0.01699  -0.0181   0.1300   1.0000
   7.250   0.8553   0.02962   0.01857  -0.0168   0.1055   1.0000
   7.500   0.8738   0.03128   0.02025  -0.0156   0.0873   1.0000
   7.750   0.8932   0.03316   0.02218  -0.0145   0.0766   1.0000
   8.000   0.9139   0.03515   0.02436  -0.0134   0.0681   1.0000
   8.250   0.9333   0.03724   0.02671  -0.0124   0.0602   1.0000
   8.500   0.9519   0.03948   0.02910  -0.0113   0.0552   1.0000
   8.750   0.9712   0.04255   0.03257  -0.0103   0.0523   1.0000
   9.000   0.9859   0.04594   0.03655  -0.0088   0.0500   1.0000
   9.250   0.9950   0.04930   0.04041  -0.0070   0.0476   1.0000
   9.500   1.0015   0.05207   0.04346  -0.0054   0.0445   1.0000
   9.750   1.0074   0.05513   0.04651  -0.0042   0.0416   1.0000
  10.000   1.0013   0.05880   0.05073  -0.0019   0.0408   1.0000
  10.250   0.9909   0.06274   0.05506   0.0003   0.0404   1.0000
  10.500   0.9762   0.06649   0.05910   0.0024   0.0403   1.0000
  10.750   0.9584   0.07060   0.06345   0.0034   0.0402   1.0000
  11.000   0.9395   0.07522   0.06826   0.0030   0.0403   1.0000
  11.250   0.9200   0.08050   0.07369   0.0012   0.0405   1.0000
  11.500   0.9005   0.08663   0.07993  -0.0021   0.0408   1.0000
  11.750   0.8824   0.09359   0.08696  -0.0065   0.0411   1.0000
  12.000   0.8659   0.10138   0.09478  -0.0117   0.0414   1.0000
  12.250   0.8530   0.10928   0.10269  -0.0166   0.0416   1.0000
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