Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S2048 (s2048-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.49 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2048-il-1000000-n5.txt
Download as CSV file: xf-s2048-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2048                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5023   0.14033   0.13855  -0.0127   1.0000   0.0027
 -12.750  -0.5002   0.13607   0.13430  -0.0140   1.0000   0.0027
 -10.750  -0.8575   0.02691   0.02409  -0.0637   0.9958   0.0032
 -10.500  -0.8372   0.02384   0.02066  -0.0653   0.9941   0.0033
 -10.250  -0.8167   0.02188   0.01844  -0.0658   0.9919   0.0034
 -10.000  -0.7936   0.02009   0.01639  -0.0664   0.9897   0.0036
  -9.750  -0.7680   0.01871   0.01479  -0.0671   0.9880   0.0037
  -9.500  -0.7406   0.01760   0.01351  -0.0680   0.9866   0.0038
  -9.250  -0.7131   0.01628   0.01199  -0.0689   0.9853   0.0040
  -9.000  -0.6839   0.01538   0.01096  -0.0699   0.9843   0.0045
  -8.750  -0.6534   0.01491   0.01045  -0.0709   0.9835   0.0048
  -8.500  -0.6222   0.01469   0.01020  -0.0719   0.9827   0.0052
  -8.250  -0.5959   0.01436   0.00983  -0.0719   0.9803   0.0056
  -8.000  -0.5684   0.01404   0.00947  -0.0721   0.9779   0.0061
  -7.750  -0.5403   0.01354   0.00888  -0.0725   0.9757   0.0064
  -7.500  -0.5111   0.01320   0.00849  -0.0731   0.9737   0.0067
  -7.250  -0.4829   0.01252   0.00771  -0.0735   0.9717   0.0071
  -7.000  -0.4540   0.01190   0.00701  -0.0741   0.9699   0.0077
  -6.750  -0.4282   0.01165   0.00674  -0.0739   0.9664   0.0081
  -6.500  -0.4017   0.01135   0.00640  -0.0737   0.9627   0.0086
  -6.250  -0.3744   0.01102   0.00603  -0.0738   0.9594   0.0092
  -6.000  -0.3463   0.01067   0.00563  -0.0740   0.9566   0.0099
  -5.750  -0.3204   0.01037   0.00529  -0.0737   0.9522   0.0105
  -5.500  -0.2943   0.01000   0.00485  -0.0733   0.9474   0.0109
  -5.250  -0.2671   0.00968   0.00448  -0.0733   0.9433   0.0113
  -5.000  -0.2404   0.00945   0.00421  -0.0731   0.9382   0.0116
  -4.750  -0.2143   0.00902   0.00372  -0.0728   0.9323   0.0122
  -4.500  -0.1880   0.00853   0.00315  -0.0725   0.9266   0.0132
  -4.250  -0.1613   0.00823   0.00280  -0.0723   0.9195   0.0139
  -4.000  -0.1341   0.00799   0.00250  -0.0722   0.9129   0.0144
  -3.750  -0.1070   0.00778   0.00224  -0.0720   0.9047   0.0148
  -3.500  -0.0797   0.00760   0.00201  -0.0718   0.8965   0.0152
  -3.250  -0.0524   0.00745   0.00180  -0.0717   0.8877   0.0157
  -3.000  -0.0250   0.00731   0.00162  -0.0715   0.8777   0.0164
  -2.750   0.0023   0.00720   0.00144  -0.0714   0.8675   0.0171
  -2.500   0.0296   0.00712   0.00129  -0.0712   0.8552   0.0179
  -2.250   0.0566   0.00704   0.00117  -0.0709   0.8400   0.0230
  -2.000   0.0830   0.00689   0.00105  -0.0706   0.8222   0.0499
  -1.750   0.1095   0.00679   0.00095  -0.0703   0.8031   0.0758
  -1.500   0.1358   0.00662   0.00086  -0.0701   0.7833   0.1245
  -1.250   0.1623   0.00648   0.00080  -0.0699   0.7647   0.1712
  -1.000   0.1887   0.00622   0.00073  -0.0698   0.7485   0.2553
  -0.750   0.2150   0.00590   0.00067  -0.0697   0.7338   0.3605
  -0.500   0.2410   0.00551   0.00064  -0.0696   0.7196   0.4938
  -0.250   0.2672   0.00529   0.00068  -0.0694   0.7044   0.5955
   0.000   0.2938   0.00524   0.00072  -0.0691   0.6862   0.6465
   0.250   0.3206   0.00527   0.00074  -0.0689   0.6666   0.6699
   0.500   0.3473   0.00534   0.00077  -0.0686   0.6428   0.6872
   0.750   0.3736   0.00546   0.00081  -0.0683   0.6119   0.7014
   1.000   0.3999   0.00560   0.00087  -0.0680   0.5796   0.7131
   1.250   0.4256   0.00580   0.00094  -0.0676   0.5383   0.7242
   1.500   0.4510   0.00605   0.00103  -0.0672   0.4917   0.7355
   1.750   0.4768   0.00626   0.00113  -0.0668   0.4537   0.7474
   2.000   0.5025   0.00648   0.00125  -0.0664   0.4153   0.7600
   2.250   0.5281   0.00670   0.00137  -0.0661   0.3782   0.7734
   2.500   0.5535   0.00694   0.00150  -0.0657   0.3398   0.7878
   2.750   0.5782   0.00724   0.00166  -0.0652   0.2936   0.8036
   3.000   0.6031   0.00749   0.00182  -0.0647   0.2572   0.8214
   3.250   0.6284   0.00767   0.00196  -0.0642   0.2337   0.8421
   3.500   0.6534   0.00778   0.00210  -0.0636   0.2172   0.8663
   3.750   0.6770   0.00793   0.00226  -0.0627   0.1965   0.8982
   4.000   0.7003   0.00804   0.00242  -0.0617   0.1771   0.9466
   4.250   0.7336   0.00829   0.00259  -0.0631   0.1549   1.0000
   4.500   0.7589   0.00860   0.00279  -0.0627   0.1297   1.0000
   4.750   0.7835   0.00899   0.00304  -0.0623   0.1006   1.0000
   5.000   0.8085   0.00934   0.00329  -0.0619   0.0797   1.0000
   5.250   0.8332   0.00972   0.00358  -0.0614   0.0600   1.0000
   5.500   0.8582   0.01007   0.00388  -0.0610   0.0465   1.0000
   5.750   0.8834   0.01038   0.00415  -0.0606   0.0377   1.0000
   6.000   0.9085   0.01071   0.00444  -0.0602   0.0304   1.0000
   6.250   0.9337   0.01100   0.00473  -0.0599   0.0252   1.0000
   6.500   0.9584   0.01137   0.00505  -0.0594   0.0192   1.0000
   6.750   0.9835   0.01167   0.00537  -0.0590   0.0164   1.0000
   7.000   1.0078   0.01206   0.00575  -0.0585   0.0123   1.0000
   7.250   1.0316   0.01251   0.00617  -0.0580   0.0077   1.0000
   7.500   1.0553   0.01296   0.00663  -0.0573   0.0054   1.0000
   7.750   1.0792   0.01338   0.00708  -0.0568   0.0045   1.0000
   8.000   1.1029   0.01381   0.00756  -0.0562   0.0040   1.0000
   8.250   1.1262   0.01427   0.00807  -0.0555   0.0036   1.0000
   8.500   1.1490   0.01479   0.00863  -0.0548   0.0032   1.0000
   8.750   1.1709   0.01539   0.00931  -0.0539   0.0027   1.0000
   9.000   1.1912   0.01619   0.01023  -0.0528   0.0024   1.0000
   9.250   1.2131   0.01675   0.01085  -0.0519   0.0024   1.0000
   9.500   1.2342   0.01737   0.01155  -0.0510   0.0023   1.0000
   9.750   1.2548   0.01801   0.01227  -0.0500   0.0023   1.0000
  10.000   1.2749   0.01867   0.01302  -0.0489   0.0022   1.0000
  10.250   1.2938   0.01943   0.01387  -0.0477   0.0021   1.0000
  10.500   1.3121   0.02022   0.01475  -0.0464   0.0021   1.0000
  10.750   1.3294   0.02104   0.01570  -0.0450   0.0020   1.0000
  11.000   1.3456   0.02193   0.01669  -0.0434   0.0019   1.0000
  11.250   1.3605   0.02285   0.01773  -0.0417   0.0019   1.0000
  11.500   1.3744   0.02378   0.01876  -0.0399   0.0018   1.0000
  11.750   1.3846   0.02473   0.01983  -0.0374   0.0017   1.0000
  12.000   1.3927   0.02575   0.02096  -0.0347   0.0017   1.0000
  12.250   1.4008   0.02678   0.02209  -0.0322   0.0016   1.0000
  12.500   1.4058   0.02804   0.02348  -0.0294   0.0016   1.0000
  12.750   1.4080   0.02955   0.02513  -0.0266   0.0016   1.0000
  13.000   1.4107   0.03105   0.02677  -0.0241   0.0016   1.0000
  13.250   1.4171   0.03232   0.02811  -0.0222   0.0014   1.0000
  13.500   1.4156   0.03430   0.03025  -0.0200   0.0014   1.0000
  13.750   1.4163   0.03620   0.03228  -0.0183   0.0014   1.0000
  14.000   1.4116   0.03874   0.03498  -0.0166   0.0014   1.0000
  14.250   1.4052   0.04164   0.03803  -0.0155   0.0014   1.0000
  14.500   1.4003   0.04463   0.04114  -0.0150   0.0013   1.0000
  14.750   1.3902   0.04850   0.04517  -0.0151   0.0013   1.0000
  15.000   1.3796   0.05285   0.04966  -0.0160   0.0013   1.0000
  15.250   1.3595   0.05910   0.05609  -0.0184   0.0012   1.0000
  15.500   1.3422   0.06579   0.06296  -0.0218   0.0013   1.0000
  15.750   1.3211   0.07408   0.07143  -0.0267   0.0013   1.0000
  16.000   1.2945   0.08442   0.08196  -0.0331   0.0014   1.0000
  16.250   1.2640   0.09615   0.09385  -0.0402   0.0013   1.0000
  16.500   1.2310   0.10853   0.10640  -0.0473   0.0014   1.0000
  16.750   1.1908   0.12279   0.12080  -0.0555   0.0014   1.0000
  17.000   1.1497   0.13787   0.13603  -0.0641   0.0015   1.0000
  17.250   1.1189   0.15124   0.14950  -0.0718   0.0015   1.0000
<< Back to S2048 (s2048-il)

Polar data table (+)

Polar graphs


<< Back to S2048 (s2048-il)