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S3025 9.38% (s3025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.15 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3025-il-1000000.txt
Download as CSV file: xf-s3025-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3491   0.08451   0.08297  -0.0327   1.0000   0.0084
  -8.000  -0.3543   0.08174   0.08024  -0.0323   1.0000   0.0088
  -7.750  -0.3572   0.07880   0.07733  -0.0329   0.9995   0.0087
  -7.500  -0.3406   0.07314   0.07167  -0.0411   0.9950   0.0091
  -7.250  -0.3166   0.06448   0.06300  -0.0551   0.9883   0.0100
  -7.000  -0.2852   0.05583   0.05428  -0.0691   0.9846   0.0101
  -6.750  -0.2675   0.03877   0.03688  -0.0855   0.9737   0.0105
  -6.500  -0.2478   0.03488   0.03281  -0.0883   0.9627   0.0108
  -6.250  -0.2255   0.03299   0.03080  -0.0898   0.9506   0.0112
  -6.000  -0.2052   0.03003   0.02762  -0.0906   0.9333   0.0118
  -5.750  -0.1867   0.02607   0.02329  -0.0903   0.9119   0.0130
  -5.500  -0.1718   0.02126   0.01770  -0.0890   0.8884   0.0144
  -5.250  -0.1508   0.01956   0.01582  -0.0884   0.8688   0.0149
  -5.000  -0.1278   0.01848   0.01458  -0.0879   0.8507   0.0154
  -4.750  -0.1038   0.01762   0.01351  -0.0874   0.8340   0.0166
  -4.500  -0.0752   0.01863   0.01430  -0.0867   0.8185   0.0186
  -4.250  -0.0553   0.01214   0.00693  -0.0845   0.8057   0.0104
  -4.000  -0.0302   0.01098   0.00562  -0.0839   0.7928   0.0100
  -3.750  -0.0046   0.01016   0.00465  -0.0833   0.7804   0.0100
  -3.500   0.0216   0.00968   0.00404  -0.0828   0.7686   0.0102
  -3.250   0.0469   0.00884   0.00306  -0.0822   0.7572   0.0108
  -3.000   0.0735   0.00847   0.00264  -0.0820   0.7464   0.0118
  -2.750   0.1005   0.00824   0.00233  -0.0817   0.7362   0.0124
  -2.250   0.1550   0.00787   0.00181  -0.0812   0.7160   0.0142
  -2.000   0.1823   0.00766   0.00154  -0.0810   0.7065   0.0170
  -1.500   0.2357   0.00700   0.00121  -0.0806   0.6873   0.1341
  -1.250   0.2624   0.00675   0.00115  -0.0805   0.6782   0.2103
  -1.000   0.2888   0.00647   0.00111  -0.0803   0.6688   0.3081
  -0.750   0.3151   0.00614   0.00109  -0.0802   0.6597   0.4235
  -0.500   0.3403   0.00575   0.00110  -0.0798   0.6507   0.5774
  -0.250   0.3644   0.00534   0.00112  -0.0790   0.6415   0.7359
   0.000   0.3839   0.00494   0.00119  -0.0768   0.6329   0.9025
   0.500   0.4650   0.00497   0.00117  -0.0821   0.6136   0.9935
   0.750   0.5032   0.00503   0.00115  -0.0844   0.6041   1.0000
   1.250   0.5540   0.00517   0.00118  -0.0833   0.5848   1.0000
   1.500   0.5795   0.00525   0.00121  -0.0827   0.5751   1.0000
   1.750   0.6049   0.00535   0.00124  -0.0822   0.5650   1.0000
   2.000   0.6308   0.00543   0.00128  -0.0817   0.5541   1.0000
   2.250   0.6567   0.00552   0.00133  -0.0813   0.5429   1.0000
   2.500   0.6826   0.00563   0.00139  -0.0809   0.5310   1.0000
   2.750   0.7086   0.00575   0.00145  -0.0805   0.5183   1.0000
   3.000   0.7346   0.00587   0.00151  -0.0801   0.5048   1.0000
   3.250   0.7606   0.00600   0.00159  -0.0798   0.4914   1.0000
   3.500   0.7867   0.00614   0.00169  -0.0794   0.4770   1.0000
   3.750   0.8127   0.00629   0.00179  -0.0791   0.4617   1.0000
   4.000   0.8386   0.00645   0.00189  -0.0787   0.4449   1.0000
   4.250   0.8642   0.00664   0.00201  -0.0783   0.4263   1.0000
   4.500   0.8896   0.00686   0.00216  -0.0779   0.4070   1.0000
   4.750   0.9151   0.00707   0.00231  -0.0776   0.3870   1.0000
   5.000   0.9405   0.00730   0.00247  -0.0772   0.3674   1.0000
   5.250   0.9651   0.00760   0.00267  -0.0767   0.3419   1.0000
   5.500   0.9891   0.00795   0.00289  -0.0761   0.3126   1.0000
   5.750   1.0125   0.00835   0.00315  -0.0754   0.2810   1.0000
   6.000   1.0365   0.00869   0.00339  -0.0749   0.2566   1.0000
   6.250   1.0600   0.00909   0.00367  -0.0743   0.2308   1.0000
   6.500   1.0832   0.00950   0.00397  -0.0736   0.2052   1.0000
   6.750   1.1064   0.00991   0.00427  -0.0729   0.1817   1.0000
   7.000   1.1289   0.01037   0.00461  -0.0722   0.1564   1.0000
   7.250   1.1511   0.01085   0.00499  -0.0714   0.1336   1.0000
   7.500   1.1727   0.01136   0.00539  -0.0705   0.1115   1.0000
   7.750   1.1931   0.01198   0.00586  -0.0695   0.0855   1.0000
   8.000   1.2117   0.01273   0.00643  -0.0682   0.0566   1.0000
   8.250   1.2255   0.01388   0.00731  -0.0661   0.0201   1.0000
   8.500   1.2448   0.01453   0.00793  -0.0648   0.0130   1.0000
   8.750   1.2652   0.01506   0.00849  -0.0637   0.0116   1.0000
   9.000   1.2842   0.01568   0.00917  -0.0624   0.0104   1.0000
   9.250   1.3028   0.01630   0.00987  -0.0610   0.0098   1.0000
   9.500   1.3216   0.01686   0.01050  -0.0597   0.0095   1.0000
   9.750   1.3393   0.01747   0.01118  -0.0582   0.0093   1.0000
  10.000   1.3555   0.01813   0.01191  -0.0565   0.0090   1.0000
  10.250   1.3689   0.01881   0.01267  -0.0543   0.0087   1.0000
  10.500   1.3801   0.01953   0.01344  -0.0518   0.0083   1.0000
  10.750   1.3899   0.02032   0.01431  -0.0492   0.0081   1.0000
  11.000   1.3975   0.02128   0.01533  -0.0465   0.0077   1.0000
  11.250   1.4022   0.02243   0.01658  -0.0436   0.0075   1.0000
  11.500   1.4032   0.02388   0.01815  -0.0404   0.0073   1.0000
  11.750   1.3945   0.02610   0.02052  -0.0367   0.0071   1.0000
  12.000   1.3940   0.02795   0.02248  -0.0343   0.0070   1.0000
  12.250   1.3985   0.02953   0.02415  -0.0326   0.0069   1.0000
  12.500   1.4057   0.03098   0.02569  -0.0313   0.0068   1.0000
  12.750   1.4076   0.03298   0.02778  -0.0299   0.0067   1.0000
  13.000   1.4131   0.03475   0.02965  -0.0290   0.0066   1.0000
  13.250   1.4123   0.03723   0.03224  -0.0279   0.0065   1.0000
  13.500   1.4158   0.03938   0.03448  -0.0273   0.0064   1.0000
  13.750   1.4158   0.04198   0.03719  -0.0268   0.0063   1.0000
  14.000   1.4162   0.04465   0.03996  -0.0265   0.0061   1.0000
  14.250   1.4168   0.04738   0.04279  -0.0264   0.0060   1.0000
  14.500   1.4158   0.05040   0.04591  -0.0266   0.0058   1.0000
  14.750   1.4122   0.05387   0.04949  -0.0269   0.0057   1.0000
  15.000   1.4110   0.05716   0.05287  -0.0275   0.0056   1.0000
  15.250   1.4055   0.06112   0.05695  -0.0282   0.0055   1.0000
  15.500   1.3993   0.06536   0.06131  -0.0292   0.0055   1.0000
  15.750   1.3958   0.06940   0.06544  -0.0306   0.0054   1.0000
  16.000   1.3892   0.07401   0.07016  -0.0321   0.0053   1.0000
  16.250   1.3824   0.07882   0.07506  -0.0339   0.0052   1.0000
  16.500   1.3749   0.08391   0.08025  -0.0359   0.0052   1.0000
  16.750   1.3663   0.08928   0.08575  -0.0381   0.0052   1.0000
  17.000   1.3561   0.09504   0.09161  -0.0406   0.0050   1.0000
  17.250   1.3455   0.10105   0.09774  -0.0433   0.0050   1.0000
  17.500   1.3282   0.10825   0.10508  -0.0464   0.0049   1.0000
  17.750   1.3163   0.11488   0.11185  -0.0497   0.0048   1.0000
  18.000   1.3032   0.12191   0.11902  -0.0534   0.0048   1.0000
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