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S3025 9.38% (s3025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.31 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3025-il-1000000-n5.txt
Download as CSV file: xf-s3025-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3025 9.38%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3587   0.09026   0.08865  -0.0321   1.0000   0.0039
  -8.750  -0.3601   0.08676   0.08516  -0.0328   1.0000   0.0039
  -8.500  -0.3620   0.07960   0.07804  -0.0376   0.9945   0.0044
  -8.250  -0.3501   0.07606   0.07450  -0.0417   0.9884   0.0042
  -7.500  -0.3090   0.05038   0.04868  -0.0779   0.9403   0.0044
  -7.000  -0.3187   0.02545   0.02254  -0.0867   0.8629   0.0043
  -6.750  -0.3088   0.02041   0.01679  -0.0860   0.8421   0.0044
  -6.500  -0.2914   0.01757   0.01345  -0.0852   0.8245   0.0045
  -6.250  -0.2695   0.01604   0.01161  -0.0846   0.8091   0.0046
  -6.000  -0.2462   0.01474   0.01002  -0.0840   0.7950   0.0046
  -5.750  -0.2221   0.01364   0.00866  -0.0835   0.7817   0.0047
  -5.500  -0.1972   0.01278   0.00759  -0.0830   0.7691   0.0047
  -5.250  -0.1718   0.01205   0.00667  -0.0826   0.7568   0.0048
  -5.000  -0.1460   0.01144   0.00592  -0.0822   0.7454   0.0049
  -4.750  -0.1199   0.01091   0.00526  -0.0819   0.7347   0.0050
  -4.500  -0.0936   0.01045   0.00468  -0.0815   0.7245   0.0052
  -4.250  -0.0671   0.01005   0.00417  -0.0812   0.7143   0.0054
  -4.000  -0.0403   0.00968   0.00371  -0.0810   0.7051   0.0057
  -3.750  -0.0135   0.00938   0.00332  -0.0807   0.6960   0.0061
  -3.500   0.0136   0.00910   0.00297  -0.0805   0.6870   0.0064
  -3.250   0.0408   0.00890   0.00269  -0.0804   0.6786   0.0066
  -3.000   0.0680   0.00868   0.00241  -0.0802   0.6699   0.0069
  -2.750   0.0952   0.00839   0.00204  -0.0800   0.6616   0.0074
  -2.250   0.1501   0.00810   0.00166  -0.0797   0.6447   0.0090
  -2.000   0.1776   0.00800   0.00149  -0.0796   0.6362   0.0096
  -1.750   0.2052   0.00790   0.00133  -0.0794   0.6268   0.0110
  -1.500   0.2327   0.00779   0.00121  -0.0793   0.6180   0.0174
  -1.250   0.2597   0.00757   0.00111  -0.0792   0.6088   0.0610
  -1.000   0.2868   0.00735   0.00104  -0.0791   0.5993   0.1174
  -0.750   0.3138   0.00718   0.00099  -0.0790   0.5900   0.1736
  -0.500   0.3409   0.00707   0.00097  -0.0789   0.5800   0.2215
  -0.250   0.3676   0.00681   0.00096  -0.0788   0.5699   0.3215
   0.000   0.3941   0.00657   0.00097  -0.0787   0.5602   0.4244
   0.250   0.4208   0.00644   0.00098  -0.0785   0.5503   0.4960
   0.500   0.4474   0.00627   0.00100  -0.0784   0.5401   0.5789
   0.750   0.4731   0.00606   0.00104  -0.0780   0.5299   0.6830
   1.000   0.4975   0.00584   0.00110  -0.0772   0.5196   0.7901
   1.250   0.5192   0.00564   0.00117  -0.0756   0.5089   0.8980
   1.500   0.5520   0.00565   0.00122  -0.0765   0.4965   0.9687
   1.750   0.5901   0.00575   0.00125  -0.0788   0.4828   0.9903
   2.000   0.6245   0.00586   0.00129  -0.0803   0.4687   1.0000
   2.250   0.6500   0.00600   0.00135  -0.0798   0.4541   1.0000
   2.500   0.6756   0.00614   0.00143  -0.0794   0.4386   1.0000
   3.000   0.7268   0.00647   0.00160  -0.0785   0.4058   1.0000
   3.250   0.7524   0.00665   0.00170  -0.0781   0.3885   1.0000
   3.500   0.7781   0.00683   0.00182  -0.0777   0.3707   1.0000
   3.750   0.8036   0.00703   0.00194  -0.0774   0.3534   1.0000
   4.000   0.8290   0.00726   0.00209  -0.0769   0.3345   1.0000
   4.250   0.8543   0.00748   0.00224  -0.0765   0.3158   1.0000
   4.500   0.8791   0.00776   0.00242  -0.0761   0.2934   1.0000
   4.750   0.9035   0.00808   0.00262  -0.0755   0.2668   1.0000
   5.000   0.9280   0.00839   0.00282  -0.0750   0.2439   1.0000
   5.250   0.9525   0.00870   0.00305  -0.0745   0.2234   1.0000
   5.500   0.9771   0.00900   0.00327  -0.0741   0.2052   1.0000
   5.750   1.0003   0.00942   0.00355  -0.0734   0.1771   1.0000
   6.000   1.0225   0.00993   0.00388  -0.0726   0.1440   1.0000
   6.250   1.0451   0.01040   0.00422  -0.0719   0.1187   1.0000
   6.500   1.0679   0.01084   0.00456  -0.0711   0.0987   1.0000
   6.750   1.0906   0.01127   0.00490  -0.0704   0.0803   1.0000
   7.000   1.1128   0.01175   0.00529  -0.0696   0.0634   1.0000
   7.250   1.1338   0.01232   0.00575  -0.0686   0.0432   1.0000
   7.500   1.1543   0.01293   0.00626  -0.0676   0.0263   1.0000
   7.750   1.1735   0.01362   0.00686  -0.0663   0.0106   1.0000
   8.000   1.1958   0.01402   0.00728  -0.0655   0.0092   1.0000
   8.250   1.2179   0.01443   0.00771  -0.0647   0.0084   1.0000
   8.500   1.2393   0.01487   0.00820  -0.0637   0.0075   1.0000
   8.750   1.2610   0.01528   0.00865  -0.0629   0.0073   1.0000
   9.000   1.2820   0.01571   0.00913  -0.0619   0.0071   1.0000
   9.250   1.3022   0.01618   0.00964  -0.0608   0.0068   1.0000
   9.500   1.3218   0.01667   0.01019  -0.0597   0.0066   1.0000
   9.750   1.3403   0.01721   0.01079  -0.0584   0.0063   1.0000
  10.000   1.3580   0.01776   0.01140  -0.0569   0.0061   1.0000
  10.250   1.3735   0.01837   0.01206  -0.0551   0.0059   1.0000
  10.500   1.3868   0.01898   0.01273  -0.0530   0.0058   1.0000
  10.750   1.3981   0.01970   0.01352  -0.0505   0.0056   1.0000
  11.000   1.4085   0.02048   0.01437  -0.0481   0.0055   1.0000
  11.250   1.4166   0.02143   0.01541  -0.0455   0.0053   1.0000
  11.500   1.4227   0.02252   0.01660  -0.0429   0.0051   1.0000
  11.750   1.4292   0.02364   0.01781  -0.0405   0.0050   1.0000
  12.000   1.4382   0.02463   0.01888  -0.0386   0.0050   1.0000
  12.250   1.4478   0.02565   0.01997  -0.0369   0.0048   1.0000
  12.500   1.4547   0.02691   0.02132  -0.0351   0.0048   1.0000
  12.750   1.4597   0.02839   0.02289  -0.0334   0.0047   1.0000
  13.000   1.4670   0.02977   0.02435  -0.0321   0.0046   1.0000
  13.250   1.4695   0.03163   0.02632  -0.0307   0.0045   1.0000
  13.500   1.4723   0.03359   0.02838  -0.0295   0.0045   1.0000
  13.750   1.4754   0.03561   0.03050  -0.0287   0.0044   1.0000
  14.000   1.4772   0.03787   0.03286  -0.0279   0.0043   1.0000
  14.250   1.4773   0.04041   0.03550  -0.0274   0.0042   1.0000
  14.500   1.4773   0.04307   0.03827  -0.0271   0.0041   1.0000
  14.750   1.4793   0.04560   0.04089  -0.0271   0.0040   1.0000
  15.000   1.4780   0.04860   0.04399  -0.0272   0.0039   1.0000
  15.250   1.4718   0.05236   0.04787  -0.0276   0.0039   1.0000
  15.500   1.4662   0.05622   0.05185  -0.0283   0.0039   1.0000
  15.750   1.4688   0.05910   0.05480  -0.0289   0.0037   1.0000
  16.000   1.4590   0.06384   0.05967  -0.0302   0.0037   1.0000
  16.250   1.4555   0.06787   0.06379  -0.0315   0.0036   1.0000
  16.500   1.4471   0.07279   0.06884  -0.0332   0.0036   1.0000
  16.750   1.4407   0.07755   0.07370  -0.0350   0.0036   1.0000
  17.000   1.4307   0.08310   0.07937  -0.0373   0.0035   1.0000
  17.250   1.4205   0.08886   0.08525  -0.0399   0.0035   1.0000
  17.500   1.4081   0.09514   0.09165  -0.0427   0.0035   1.0000
  17.750   1.3950   0.10175   0.09840  -0.0459   0.0035   1.0000
  18.000   1.3838   0.10819   0.10494  -0.0491   0.0034   1.0000
  18.250   1.3704   0.11512   0.11199  -0.0526   0.0034   1.0000
  18.500   1.3554   0.12251   0.11951  -0.0565   0.0034   1.0000
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