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S2027 (s2027-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S2027 (s2027-il)
Reynolds number: 100,000
Max Cl/Cd: 45.95 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2027-il-100000.txt
Download as CSV file: xf-s2027-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2027                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3613   0.10532   0.10065  -0.0370   1.0000   0.1395
 -10.000  -0.3457   0.10250   0.09783  -0.0361   1.0000   0.1441
  -9.750  -0.3900   0.09887   0.09440  -0.0439   1.0000   0.1515
  -9.500  -0.3573   0.09502   0.09053  -0.0401   1.0000   0.1544
  -9.250  -0.3467   0.09207   0.08760  -0.0397   1.0000   0.1579
  -7.750  -0.5938   0.05941   0.05491  -0.0476   0.9911   0.0968
  -7.500  -0.5916   0.04768   0.04165  -0.0514   0.9805   0.0674
  -7.250  -0.5655   0.04298   0.03663  -0.0539   0.9729   0.0661
  -7.000  -0.5385   0.03896   0.03217  -0.0558   0.9651   0.0642
  -6.750  -0.5053   0.03543   0.02810  -0.0580   0.9581   0.0628
  -6.500  -0.4751   0.03286   0.02505  -0.0591   0.9499   0.0624
  -6.250  -0.4349   0.03055   0.02237  -0.0616   0.9438   0.0630
  -6.000  -0.4018   0.02887   0.02043  -0.0625   0.9356   0.0647
  -5.750  -0.3596   0.02723   0.01859  -0.0651   0.9297   0.0691
  -5.500  -0.3265   0.02589   0.01735  -0.0664   0.9217   0.0746
  -5.250  -0.2855   0.02463   0.01600  -0.0685   0.9155   0.0811
  -5.000  -0.2581   0.02343   0.01491  -0.0687   0.9066   0.0939
  -4.750  -0.2319   0.02110   0.01335  -0.0691   0.8993   0.1806
  -4.500  -0.2185   0.01973   0.01301  -0.0675   0.8884   0.3675
  -4.250  -0.1839   0.01941   0.01302  -0.0682   0.8826   0.4807
  -4.000  -0.1654   0.01972   0.01348  -0.0658   0.8712   0.5459
  -3.750  -0.1414   0.02010   0.01388  -0.0641   0.8620   0.5928
  -3.500  -0.1112   0.02028   0.01402  -0.0633   0.8546   0.6274
  -3.250  -0.0894   0.02051   0.01419  -0.0614   0.8445   0.6545
  -3.000  -0.0583   0.02051   0.01409  -0.0608   0.8383   0.6819
  -2.750  -0.0385   0.02073   0.01430  -0.0585   0.8277   0.7025
  -2.500  -0.0081   0.02064   0.01410  -0.0576   0.8222   0.7260
  -2.250   0.0103   0.02080   0.01423  -0.0553   0.8111   0.7452
  -2.000   0.0335   0.02084   0.01422  -0.0535   0.8028   0.7636
  -1.750   0.0579   0.02078   0.01409  -0.0519   0.7948   0.7819
  -1.500   0.0784   0.02085   0.01410  -0.0500   0.7854   0.7998
  -1.250   0.1045   0.02067   0.01384  -0.0486   0.7787   0.8177
  -1.000   0.1238   0.02075   0.01387  -0.0467   0.7687   0.8351
  -0.750   0.1519   0.02052   0.01354  -0.0455   0.7628   0.8512
  -0.500   0.1725   0.02061   0.01361  -0.0439   0.7524   0.8676
  -0.250   0.2050   0.02034   0.01323  -0.0435   0.7470   0.8834
   0.000   0.2310   0.02045   0.01332  -0.0431   0.7364   0.8998
   0.250   0.2700   0.02023   0.01299  -0.0444   0.7303   0.9146
   0.500   0.3086   0.02026   0.01296  -0.0464   0.7205   0.9293
   0.750   0.3538   0.02017   0.01279  -0.0495   0.7122   0.9428
   1.000   0.4027   0.01999   0.01251  -0.0533   0.7041   0.9554
   1.250   0.4576   0.01994   0.01240  -0.0588   0.6942   0.9653
   1.500   0.5112   0.01955   0.01189  -0.0634   0.6870   0.9760
   1.750   0.5601   0.01953   0.01186  -0.0683   0.6758   0.9887
   2.000   0.6074   0.01940   0.01168  -0.0726   0.6663   1.0000
   2.250   0.6212   0.01935   0.01156  -0.0708   0.6583   1.0000
   2.500   0.6285   0.01963   0.01186  -0.0683   0.6485   1.0000
   2.750   0.6442   0.01953   0.01165  -0.0664   0.6420   1.0000
   3.000   0.6511   0.01994   0.01209  -0.0637   0.6316   1.0000
   3.250   0.6703   0.02005   0.01211  -0.0623   0.6241   1.0000
   3.500   0.6897   0.02029   0.01231  -0.0610   0.6147   1.0000
   3.750   0.7108   0.02061   0.01260  -0.0601   0.6054   1.0000
   4.000   0.7382   0.02063   0.01255  -0.0598   0.5979   1.0000
   4.250   0.7588   0.02108   0.01303  -0.0589   0.5876   1.0000
   4.500   0.7874   0.02112   0.01299  -0.0587   0.5802   1.0000
   4.750   0.8098   0.02149   0.01339  -0.0580   0.5701   1.0000
   5.000   0.8334   0.02186   0.01379  -0.0575   0.5607   1.0000
   5.250   0.8625   0.02191   0.01378  -0.0574   0.5529   1.0000
   5.500   0.8833   0.02242   0.01437  -0.0566   0.5424   1.0000
   5.750   0.9109   0.02261   0.01454  -0.0563   0.5342   1.0000
   6.000   0.9354   0.02292   0.01488  -0.0558   0.5246   1.0000
   6.250   0.9576   0.02340   0.01544  -0.0551   0.5147   1.0000
   6.500   0.9890   0.02340   0.01535  -0.0553   0.5071   1.0000
   6.750   1.0081   0.02401   0.01612  -0.0543   0.4961   1.0000
   7.000   1.0319   0.02443   0.01659  -0.0537   0.4868   1.0000
   7.250   1.0610   0.02453   0.01666  -0.0536   0.4781   1.0000
   7.500   1.0800   0.02517   0.01744  -0.0526   0.4674   1.0000
   7.750   1.1049   0.02551   0.01783  -0.0521   0.4581   1.0000
   8.000   1.1321   0.02571   0.01803  -0.0518   0.4487   1.0000
   8.250   1.1506   0.02634   0.01882  -0.0507   0.4380   1.0000
   8.500   1.1748   0.02671   0.01923  -0.0501   0.4283   1.0000
   8.750   1.2029   0.02684   0.01937  -0.0499   0.4185   1.0000
   9.000   1.2197   0.02748   0.02017  -0.0485   0.4071   1.0000
   9.250   1.2402   0.02789   0.02067  -0.0475   0.3959   1.0000
   9.500   1.2637   0.02808   0.02088  -0.0467   0.3844   1.0000
   9.750   1.2884   0.02817   0.02094  -0.0461   0.3723   1.0000
  10.000   1.3073   0.02845   0.02131  -0.0448   0.3595   1.0000
  10.250   1.3215   0.02888   0.02185  -0.0429   0.3463   1.0000
  10.500   1.3351   0.02931   0.02238  -0.0410   0.3331   1.0000
  10.750   1.3474   0.02975   0.02290  -0.0389   0.3197   1.0000
  11.000   1.3575   0.03025   0.02347  -0.0367   0.3063   1.0000
  11.250   1.3650   0.03083   0.02412  -0.0341   0.2930   1.0000
  11.500   1.3681   0.03147   0.02484  -0.0310   0.2801   1.0000
  11.750   1.3682   0.03227   0.02568  -0.0277   0.2673   1.0000
  12.000   1.3651   0.03330   0.02674  -0.0245   0.2538   1.0000
  12.250   1.3593   0.03463   0.02811  -0.0216   0.2400   1.0000
  12.500   1.3509   0.03633   0.02985  -0.0190   0.2256   1.0000
  12.750   1.3401   0.03847   0.03203  -0.0169   0.2107   1.0000
  13.000   1.3284   0.04102   0.03461  -0.0152   0.1954   1.0000
  13.250   1.3155   0.04400   0.03760  -0.0140   0.1798   1.0000
  13.500   1.3018   0.04739   0.04097  -0.0133   0.1644   1.0000
  13.750   1.2878   0.05112   0.04465  -0.0130   0.1498   1.0000
  14.000   1.2741   0.05509   0.04858  -0.0130   0.1363   1.0000
  14.250   1.2601   0.05939   0.05284  -0.0134   0.1235   1.0000
  14.500   1.2486   0.06364   0.05703  -0.0138   0.1120   1.0000
  14.750   1.2370   0.06809   0.06143  -0.0145   0.1013   1.0000
  15.000   1.2279   0.07231   0.06555  -0.0152   0.0917   1.0000
  15.250   1.2197   0.07666   0.06992  -0.0161   0.0832   1.0000
  15.500   1.2140   0.08077   0.07406  -0.0167   0.0749   1.0000
  15.750   1.2141   0.08395   0.07713  -0.0166   0.0674   1.0000
  16.000   1.2117   0.08782   0.08109  -0.0174   0.0617   1.0000
  16.250   1.2174   0.09040   0.08365  -0.0170   0.0564   1.0000
  16.500   1.2126   0.09485   0.08831  -0.0184   0.0530   1.0000
  16.750   1.2175   0.09764   0.09106  -0.0187   0.0497   1.0000
  17.000   1.2270   0.10013   0.09361  -0.0180   0.0470   1.0000
  17.250   1.2200   0.10521   0.09897  -0.0198   0.0460   1.0000
  17.500   1.2111   0.11072   0.10474  -0.0221   0.0451   1.0000
  17.750   1.1997   0.11678   0.11104  -0.0248   0.0445   1.0000
  18.000   1.1845   0.12365   0.11815  -0.0284   0.0442   1.0000
  18.250   1.1648   0.13167   0.12643  -0.0330   0.0443   1.0000
  18.500   1.1397   0.14119   0.13620  -0.0389   0.0448   1.0000
  18.750   1.1076   0.15292   0.14815  -0.0465   0.0456   1.0000
  19.000   1.0726   0.16635   0.16172  -0.0553   0.0468   1.0000
  19.250   1.0401   0.18062   0.17604  -0.0640   0.0479   1.0000
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