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S3025 9.38% (s3025-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 500,000
Max Cl/Cd: 99.4 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3025-il-500000-n5.txt
Download as CSV file: xf-s3025-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3469   0.08652   0.08432  -0.0349   1.0000   0.0100
  -8.250  -0.3480   0.08365   0.08148  -0.0352   1.0000   0.0099
  -8.000  -0.3511   0.08172   0.07959  -0.0338   1.0000   0.0092
  -7.750  -0.3422   0.07724   0.07513  -0.0383   0.9943   0.0085
  -7.500  -0.3306   0.07150   0.06940  -0.0458   0.9854   0.0081
  -7.250  -0.3144   0.06355   0.06143  -0.0575   0.9745   0.0077
  -7.000  -0.2951   0.05223   0.04998  -0.0724   0.9603   0.0073
  -6.750  -0.2724   0.04704   0.04467  -0.0787   0.9462   0.0076
  -6.500  -0.2523   0.03976   0.03712  -0.0845   0.9276   0.0077
  -5.500  -0.1821   0.01848   0.01344  -0.0858   0.8491   0.0068
  -5.250  -0.1594   0.01663   0.01118  -0.0851   0.8337   0.0068
  -5.000  -0.1359   0.01498   0.00917  -0.0843   0.8192   0.0069
  -4.750  -0.1115   0.01378   0.00770  -0.0837   0.8055   0.0070
  -4.500  -0.0865   0.01288   0.00661  -0.0832   0.7928   0.0073
  -4.250  -0.0609   0.01224   0.00584  -0.0827   0.7804   0.0076
  -4.000  -0.0351   0.01171   0.00517  -0.0823   0.7689   0.0079
  -3.750  -0.0090   0.01124   0.00459  -0.0819   0.7573   0.0084
  -3.500   0.0173   0.01082   0.00405  -0.0815   0.7465   0.0088
  -3.250   0.0438   0.01049   0.00362  -0.0812   0.7363   0.0094
  -2.750   0.0971   0.00985   0.00281  -0.0806   0.7166   0.0112
  -2.500   0.1240   0.00962   0.00248  -0.0803   0.7075   0.0120
  -2.250   0.1511   0.00946   0.00222  -0.0800   0.6982   0.0132
  -2.000   0.1784   0.00929   0.00199  -0.0798   0.6893   0.0156
  -1.750   0.2052   0.00904   0.00179  -0.0796   0.6806   0.0383
  -1.500   0.2316   0.00870   0.00167  -0.0794   0.6715   0.1054
  -1.250   0.2583   0.00847   0.00158  -0.0793   0.6626   0.1644
  -0.750   0.3107   0.00787   0.00149  -0.0789   0.6441   0.3583
  -0.500   0.3363   0.00754   0.00148  -0.0787   0.6351   0.4771
  -0.250   0.3615   0.00725   0.00147  -0.0782   0.6255   0.5904
   0.000   0.3858   0.00694   0.00149  -0.0774   0.6162   0.7066
   0.250   0.4067   0.00661   0.00154  -0.0756   0.6070   0.8431
   0.500   0.4427   0.00652   0.00156  -0.0768   0.5964   0.9578
   0.750   0.4840   0.00657   0.00153  -0.0798   0.5853   0.9898
   1.000   0.5179   0.00664   0.00152  -0.0811   0.5749   1.0000
   1.250   0.5432   0.00674   0.00154  -0.0806   0.5648   1.0000
   1.500   0.5689   0.00684   0.00158  -0.0801   0.5538   1.0000
   1.750   0.5947   0.00694   0.00162  -0.0796   0.5432   1.0000
   2.000   0.6204   0.00705   0.00167  -0.0792   0.5321   1.0000
   2.250   0.6461   0.00717   0.00173  -0.0787   0.5203   1.0000
   2.750   0.6976   0.00744   0.00188  -0.0779   0.4945   1.0000
   3.000   0.7232   0.00759   0.00197  -0.0774   0.4798   1.0000
   3.250   0.7487   0.00775   0.00207  -0.0770   0.4643   1.0000
   3.500   0.7742   0.00793   0.00220  -0.0766   0.4475   1.0000
   3.750   0.7996   0.00812   0.00232  -0.0761   0.4307   1.0000
   4.000   0.8248   0.00833   0.00247  -0.0757   0.4129   1.0000
   4.250   0.8499   0.00855   0.00264  -0.0752   0.3951   1.0000
   4.500   0.8747   0.00880   0.00281  -0.0747   0.3762   1.0000
   4.750   0.8994   0.00906   0.00301  -0.0742   0.3558   1.0000
   5.000   0.9237   0.00936   0.00322  -0.0736   0.3348   1.0000
   5.250   0.9481   0.00966   0.00347  -0.0731   0.3142   1.0000
   5.500   0.9717   0.01001   0.00373  -0.0725   0.2915   1.0000
   5.750   0.9946   0.01043   0.00403  -0.0718   0.2638   1.0000
   6.000   1.0178   0.01083   0.00433  -0.0711   0.2391   1.0000
   6.250   1.0402   0.01129   0.00468  -0.0703   0.2120   1.0000
   6.500   1.0614   0.01186   0.00508  -0.0694   0.1798   1.0000
   6.750   1.0832   0.01235   0.00546  -0.0686   0.1551   1.0000
   7.000   1.1051   0.01284   0.00586  -0.0678   0.1345   1.0000
   7.250   1.1262   0.01337   0.00632  -0.0668   0.1144   1.0000
   7.500   1.1461   0.01400   0.00682  -0.0658   0.0902   1.0000
   7.750   1.1660   0.01461   0.00734  -0.0647   0.0709   1.0000
   8.000   1.1849   0.01528   0.00792  -0.0634   0.0524   1.0000
   8.250   1.2019   0.01608   0.00860  -0.0619   0.0323   1.0000
   8.500   1.2174   0.01698   0.00941  -0.0602   0.0153   1.0000
   8.750   1.2355   0.01763   0.01008  -0.0588   0.0123   1.0000
   9.000   1.2535   0.01825   0.01075  -0.0574   0.0110   1.0000
   9.250   1.2716   0.01883   0.01140  -0.0560   0.0103   1.0000
   9.500   1.2885   0.01943   0.01208  -0.0545   0.0097   1.0000
   9.750   1.3025   0.02009   0.01282  -0.0525   0.0092   1.0000
  10.000   1.3151   0.02081   0.01363  -0.0503   0.0088   1.0000
  10.250   1.3263   0.02162   0.01453  -0.0480   0.0085   1.0000
  10.500   1.3365   0.02250   0.01550  -0.0457   0.0082   1.0000
  10.750   1.3438   0.02360   0.01669  -0.0432   0.0079   1.0000
  11.000   1.3496   0.02484   0.01803  -0.0407   0.0077   1.0000
  11.250   1.3548   0.02616   0.01946  -0.0384   0.0075   1.0000
  11.500   1.3608   0.02749   0.02089  -0.0364   0.0075   1.0000
  11.750   1.3667   0.02890   0.02242  -0.0347   0.0074   1.0000
  12.000   1.3705   0.03057   0.02420  -0.0330   0.0073   1.0000
  12.250   1.3751   0.03227   0.02602  -0.0316   0.0071   1.0000
  12.500   1.3780   0.03422   0.02809  -0.0304   0.0070   1.0000
  12.750   1.3801   0.03636   0.03034  -0.0294   0.0069   1.0000
  13.000   1.3832   0.03849   0.03258  -0.0286   0.0066   1.0000
  13.250   1.3825   0.04112   0.03534  -0.0280   0.0065   1.0000
  13.500   1.3824   0.04381   0.03814  -0.0276   0.0064   1.0000
  13.750   1.3825   0.04657   0.04102  -0.0275   0.0062   1.0000
  14.000   1.3805   0.04968   0.04425  -0.0275   0.0061   1.0000
  14.250   1.3775   0.05304   0.04772  -0.0278   0.0060   1.0000
  14.500   1.3736   0.05664   0.05146  -0.0283   0.0059   1.0000
  14.750   1.3694   0.06039   0.05533  -0.0290   0.0059   1.0000
  15.000   1.3647   0.06438   0.05945  -0.0300   0.0058   1.0000
  15.250   1.3589   0.06870   0.06389  -0.0311   0.0058   1.0000
  15.500   1.3528   0.07317   0.06849  -0.0326   0.0057   1.0000
  15.750   1.3464   0.07789   0.07332  -0.0343   0.0056   1.0000
  16.000   1.3394   0.08285   0.07841  -0.0361   0.0056   1.0000
  16.250   1.3314   0.08809   0.08377  -0.0382   0.0055   1.0000
  16.500   1.3239   0.09340   0.08921  -0.0405   0.0055   1.0000
  16.750   1.3155   0.09901   0.09493  -0.0430   0.0054   1.0000
  17.000   1.3068   0.10480   0.10085  -0.0457   0.0053   1.0000
  17.250   1.2976   0.11076   0.10692  -0.0486   0.0053   1.0000
  17.500   1.2880   0.11691   0.11320  -0.0516   0.0052   1.0000
  17.750   1.2791   0.12308   0.11950  -0.0548   0.0052   1.0000
  18.000   1.2681   0.12972   0.12627  -0.0583   0.0051   1.0000
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