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S3025 9.38% (s3025-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 100,000
Max Cl/Cd: 56.96 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3025-il-100000.txt
Download as CSV file: xf-s3025-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3704   0.12528   0.12012  -0.0279   1.0000   0.0676
 -10.250  -0.3768   0.12401   0.11893  -0.0312   1.0000   0.0681
 -10.000  -0.3823   0.12230   0.11730  -0.0341   1.0000   0.0684
  -9.750  -0.3542   0.11402   0.10898  -0.0295   1.0000   0.0708
  -9.500  -0.3455   0.11075   0.10571  -0.0292   1.0000   0.0730
  -9.250  -0.3409   0.10783   0.10283  -0.0296   1.0000   0.0755
  -9.000  -0.3397   0.10510   0.10016  -0.0307   1.0000   0.0784
  -8.750  -0.2595   0.09158   0.08714  -0.0343   1.0000   0.0855
  -8.500  -0.2557   0.08854   0.08414  -0.0337   1.0000   0.0884
  -8.250  -0.2574   0.08570   0.08135  -0.0336   1.0000   0.0912
  -8.000  -0.3419   0.09358   0.08893  -0.0332   1.0000   0.0852
  -7.750  -0.3380   0.09094   0.08635  -0.0323   1.0000   0.0878
  -7.500  -0.3416   0.08862   0.08412  -0.0319   1.0000   0.0906
  -7.250  -0.3531   0.08680   0.08242  -0.0313   1.0000   0.0928
  -7.000  -0.3705   0.08508   0.08084  -0.0337   1.0000   0.0949
  -6.750  -0.3923   0.08336   0.07914  -0.0403   1.0000   0.0960
  -6.500  -0.3885   0.07923   0.07515  -0.0350   1.0000   0.0973
  -6.250  -0.3862   0.07701   0.07301  -0.0301   1.0000   0.0994
  -6.000  -0.3909   0.07509   0.07115  -0.0277   1.0000   0.1020
  -5.750  -0.3975   0.07308   0.06919  -0.0269   1.0000   0.1049
  -5.500  -0.4058   0.06981   0.06571  -0.0350   1.0000   0.1109
  -5.250  -0.4050   0.06714   0.06320  -0.0305   1.0000   0.1125
  -5.000  -0.4004   0.06504   0.06114  -0.0283   0.9994   0.1156
  -4.750  -0.3613   0.05963   0.05552  -0.0378   0.9917   0.1279
  -4.500  -0.3228   0.05517   0.05089  -0.0448   0.9846   0.1423
  -4.250  -0.2815   0.05242   0.04770  -0.0525   0.9751   0.1682
  -3.750  -0.1886   0.03638   0.02989  -0.0635   0.9626   0.0814
  -3.500  -0.1450   0.03107   0.02394  -0.0666   0.9585   0.0662
  -3.250  -0.1111   0.02805   0.02042  -0.0678   0.9500   0.0618
  -3.000  -0.0661   0.02540   0.01711  -0.0703   0.9451   0.0597
  -2.750  -0.0318   0.02379   0.01521  -0.0712   0.9363   0.0608
  -2.500   0.0136   0.02261   0.01373  -0.0739   0.9308   0.0683
  -2.250   0.0452   0.02119   0.01243  -0.0746   0.9216   0.0776
  -2.000   0.0887   0.01960   0.01105  -0.0771   0.9165   0.1194
  -1.750   0.1110   0.01698   0.01062  -0.0764   0.9079   0.5611
  -1.500   0.1819   0.01589   0.01011  -0.0828   0.9061   1.0000
  -1.250   0.2270   0.01582   0.00965  -0.0861   0.8994   1.0000
  -1.000   0.2634   0.01580   0.00936  -0.0876   0.8899   1.0000
  -0.750   0.2969   0.01584   0.00916  -0.0886   0.8801   1.0000
  -0.500   0.3389   0.01569   0.00879  -0.0909   0.8733   1.0000
  -0.250   0.3669   0.01579   0.00873  -0.0908   0.8621   1.0000
   0.000   0.3983   0.01581   0.00860  -0.0912   0.8523   1.0000
   0.250   0.4340   0.01570   0.00835  -0.0922   0.8441   1.0000
   0.500   0.4597   0.01585   0.00839  -0.0916   0.8324   1.0000
   0.750   0.4871   0.01595   0.00839  -0.0912   0.8216   1.0000
   1.000   0.5187   0.01590   0.00824  -0.0913   0.8125   1.0000
   1.250   0.5450   0.01601   0.00827  -0.0906   0.8011   1.0000
   1.500   0.5698   0.01618   0.00837  -0.0897   0.7891   1.0000
   1.750   0.5958   0.01631   0.00846  -0.0890   0.7777   1.0000
   2.000   0.6235   0.01638   0.00846  -0.0884   0.7670   1.0000
   2.250   0.6509   0.01644   0.00846  -0.0878   0.7560   1.0000
   2.500   0.6751   0.01663   0.00863  -0.0868   0.7433   1.0000
   2.750   0.6999   0.01681   0.00881  -0.0859   0.7307   1.0000
   3.000   0.7252   0.01698   0.00895  -0.0851   0.7183   1.0000
   3.250   0.7510   0.01711   0.00906  -0.0843   0.7060   1.0000
   3.500   0.7773   0.01722   0.00915  -0.0835   0.6937   1.0000
   3.750   0.8041   0.01731   0.00923  -0.0828   0.6814   1.0000
   4.000   0.8294   0.01744   0.00937  -0.0819   0.6677   1.0000
   4.250   0.8543   0.01759   0.00952  -0.0809   0.6534   1.0000
   4.500   0.8794   0.01771   0.00969  -0.0800   0.6387   1.0000
   4.750   0.9047   0.01783   0.00981  -0.0791   0.6236   1.0000
   5.000   0.9283   0.01799   0.01001  -0.0779   0.6068   1.0000
   5.250   0.9521   0.01814   0.01021  -0.0768   0.5893   1.0000
   5.500   0.9762   0.01826   0.01039  -0.0757   0.5714   1.0000
   5.750   1.0009   0.01837   0.01050  -0.0747   0.5533   1.0000
   6.000   1.0247   0.01852   0.01067  -0.0735   0.5339   1.0000
   6.250   1.0470   0.01872   0.01092  -0.0722   0.5125   1.0000
   6.500   1.0704   0.01891   0.01111  -0.0710   0.4914   1.0000
   6.750   1.0916   0.01919   0.01143  -0.0696   0.4676   1.0000
   7.000   1.1125   0.01953   0.01178  -0.0681   0.4433   1.0000
   7.250   1.1333   0.01992   0.01216  -0.0667   0.4188   1.0000
   7.500   1.1527   0.02040   0.01262  -0.0651   0.3930   1.0000
   7.750   1.1708   0.02098   0.01321  -0.0634   0.3662   1.0000
   8.000   1.1881   0.02164   0.01386  -0.0616   0.3393   1.0000
   8.250   1.2043   0.02239   0.01458  -0.0598   0.3124   1.0000
   8.500   1.2189   0.02321   0.01538  -0.0577   0.2853   1.0000
   8.750   1.2307   0.02403   0.01616  -0.0554   0.2574   1.0000
   9.000   1.2403   0.02488   0.01698  -0.0529   0.2294   1.0000
   9.250   1.2480   0.02580   0.01788  -0.0503   0.2023   1.0000
   9.500   1.2540   0.02685   0.01890  -0.0475   0.1757   1.0000
   9.750   1.2569   0.02813   0.02010  -0.0444   0.1517   1.0000
  10.000   1.2545   0.02976   0.02164  -0.0408   0.1249   1.0000
  10.250   1.2468   0.03209   0.02383  -0.0369   0.0959   1.0000
  10.500   1.2388   0.03475   0.02636  -0.0335   0.0768   1.0000
  10.750   1.2372   0.03721   0.02878  -0.0310   0.0658   1.0000
  11.000   1.2403   0.03959   0.03119  -0.0289   0.0588   1.0000
  11.250   1.2449   0.04185   0.03341  -0.0273   0.0536   1.0000
  11.500   1.2603   0.04429   0.03594  -0.0258   0.0500   1.0000
  11.750   1.2761   0.04668   0.03854  -0.0246   0.0473   1.0000
  12.000   1.2917   0.04926   0.04128  -0.0235   0.0452   1.0000
  12.250   1.3093   0.05226   0.04436  -0.0228   0.0432   1.0000
  12.500   1.3214   0.05654   0.04885  -0.0221   0.0416   1.0000
  12.750   1.3145   0.05950   0.05217  -0.0204   0.0410   1.0000
  13.000   1.3058   0.06302   0.05606  -0.0191   0.0405   1.0000
  13.250   1.2945   0.06694   0.06030  -0.0183   0.0401   1.0000
  13.500   1.2811   0.07132   0.06498  -0.0181   0.0400   1.0000
  13.750   1.2652   0.07622   0.07018  -0.0185   0.0401   1.0000
  14.000   1.2472   0.08153   0.07575  -0.0196   0.0401   1.0000
  14.250   1.2281   0.08731   0.08177  -0.0214   0.0404   1.0000
  14.500   1.2065   0.09371   0.08840  -0.0241   0.0406   1.0000
  14.750   1.1840   0.10074   0.09563  -0.0275   0.0408   1.0000
  15.000   1.1620   0.10822   0.10325  -0.0316   0.0412   1.0000
  15.250   1.1395   0.11645   0.11164  -0.0365   0.0415   1.0000
  15.500   1.1189   0.12513   0.12042  -0.0416   0.0419   1.0000
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