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S3025 9.38% (s3025-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 50,000
Max Cl/Cd: 39.17 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3025-il-50000-n5.txt
Download as CSV file: xf-s3025-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3511   0.11013   0.10322  -0.0303   1.0000   0.1078
  -8.750  -0.3632   0.10886   0.10210  -0.0330   1.0000   0.1094
  -8.500  -0.3738   0.10706   0.10045  -0.0349   1.0000   0.1098
  -8.250  -0.3544   0.10160   0.09500  -0.0329   1.0000   0.1112
  -8.000  -0.3494   0.09825   0.09170  -0.0324   1.0000   0.1123
  -7.750  -0.3499   0.09544   0.08900  -0.0322   1.0000   0.1128
  -7.500  -0.3539   0.09288   0.08655  -0.0320   1.0000   0.1130
  -7.000  -0.3629   0.08234   0.07611  -0.0376   1.0000   0.0534
  -6.750  -0.3637   0.07925   0.07311  -0.0373   1.0000   0.0515
  -6.500  -0.3660   0.07606   0.07000  -0.0377   1.0000   0.0498
  -6.250  -0.3689   0.07250   0.06649  -0.0386   1.0000   0.0479
  -5.750  -0.3699   0.06279   0.05650  -0.0437   1.0000   0.0425
  -5.500  -0.3667   0.05994   0.05363  -0.0429   1.0000   0.0420
  -5.250  -0.3619   0.05674   0.05034  -0.0426   1.0000   0.0414
  -5.000  -0.3497   0.05308   0.04650  -0.0438   0.9984   0.0408
  -4.750  -0.3159   0.04800   0.04099  -0.0492   0.9899   0.0401
  -4.500  -0.2812   0.04332   0.03577  -0.0537   0.9818   0.0396
  -4.250  -0.2452   0.03932   0.03115  -0.0574   0.9740   0.0398
  -4.000  -0.2104   0.03601   0.02712  -0.0599   0.9654   0.0416
  -3.750  -0.1724   0.03312   0.02358  -0.0625   0.9587   0.0436
  -3.500  -0.1404   0.03094   0.02108  -0.0638   0.9496   0.0457
  -3.250  -0.1044   0.02905   0.01879  -0.0654   0.9422   0.0479
  -3.000  -0.0697   0.02745   0.01685  -0.0664   0.9339   0.0515
  -2.750  -0.0357   0.02619   0.01538  -0.0674   0.9256   0.0590
  -2.500   0.0014   0.02502   0.01400  -0.0690   0.9183   0.0712
  -2.250   0.0345   0.02396   0.01293  -0.0700   0.9091   0.1019
  -2.000   0.0727   0.02216   0.01201  -0.0726   0.9030   0.2597
  -1.750   0.0958   0.02066   0.01179  -0.0717   0.8935   0.5400
  -1.500   0.1538   0.01950   0.01121  -0.0754   0.8896   1.0000
  -1.250   0.1853   0.01961   0.01083  -0.0762   0.8788   1.0000
  -1.000   0.2195   0.01969   0.01052  -0.0774   0.8695   1.0000
  -0.750   0.2535   0.01978   0.01026  -0.0785   0.8602   1.0000
  -0.500   0.2824   0.01993   0.01012  -0.0787   0.8492   1.0000
  -0.250   0.3137   0.02006   0.00999  -0.0793   0.8396   1.0000
   0.000   0.3464   0.02015   0.00985  -0.0801   0.8304   1.0000
   0.250   0.3734   0.02035   0.00986  -0.0799   0.8192   1.0000
   0.500   0.4025   0.02053   0.00987  -0.0800   0.8090   1.0000
   0.750   0.4353   0.02060   0.00979  -0.0807   0.8003   1.0000
   1.000   0.4607   0.02086   0.00992  -0.0802   0.7886   1.0000
   1.250   0.4874   0.02108   0.01004  -0.0799   0.7775   1.0000
   1.500   0.5166   0.02123   0.01009  -0.0799   0.7675   1.0000
   1.750   0.5452   0.02138   0.01017  -0.0797   0.7571   1.0000
   2.000   0.5701   0.02165   0.01040  -0.0791   0.7450   1.0000
   2.250   0.5960   0.02189   0.01060  -0.0785   0.7334   1.0000
   2.500   0.6232   0.02208   0.01075  -0.0781   0.7223   1.0000
   2.750   0.6524   0.02218   0.01084  -0.0779   0.7119   1.0000
   3.000   0.6764   0.02247   0.01113  -0.0770   0.6990   1.0000
   3.250   0.7009   0.02274   0.01141  -0.0762   0.6862   1.0000
   3.500   0.7257   0.02299   0.01169  -0.0754   0.6734   1.0000
   3.750   0.7508   0.02323   0.01200  -0.0747   0.6605   1.0000
   4.000   0.7760   0.02346   0.01226  -0.0739   0.6475   1.0000
   4.250   0.8011   0.02368   0.01253  -0.0731   0.6341   1.0000
   4.500   0.8259   0.02391   0.01282  -0.0722   0.6203   1.0000
   4.750   0.8503   0.02415   0.01317  -0.0712   0.6060   1.0000
   5.000   0.8740   0.02440   0.01351  -0.0702   0.5910   1.0000
   5.250   0.8973   0.02467   0.01387  -0.0691   0.5753   1.0000
   5.500   0.9204   0.02495   0.01428  -0.0680   0.5591   1.0000
   5.750   0.9434   0.02521   0.01464  -0.0668   0.5422   1.0000
   6.000   0.9667   0.02544   0.01497  -0.0656   0.5248   1.0000
   6.250   0.9894   0.02569   0.01530  -0.0644   0.5068   1.0000
   6.500   1.0094   0.02611   0.01589  -0.0629   0.4866   1.0000
   6.750   1.0309   0.02643   0.01630  -0.0615   0.4669   1.0000
   7.000   1.0509   0.02686   0.01683  -0.0600   0.4461   1.0000
   7.250   1.0704   0.02733   0.01738  -0.0584   0.4245   1.0000
   7.500   1.0889   0.02788   0.01802  -0.0568   0.4026   1.0000
   7.750   1.1067   0.02848   0.01872  -0.0551   0.3803   1.0000
   8.000   1.1228   0.02921   0.01954  -0.0533   0.3575   1.0000
   8.250   1.1387   0.02996   0.02031  -0.0515   0.3355   1.0000
   8.500   1.1522   0.03091   0.02136  -0.0495   0.3129   1.0000
   8.750   1.1653   0.03187   0.02233  -0.0475   0.2918   1.0000
   9.000   1.1761   0.03302   0.02360  -0.0454   0.2704   1.0000
   9.250   1.1857   0.03419   0.02483  -0.0432   0.2505   1.0000
   9.500   1.1928   0.03553   0.02627  -0.0408   0.2307   1.0000
   9.750   1.1968   0.03693   0.02774  -0.0382   0.2122   1.0000
  10.000   1.1991   0.03848   0.02930  -0.0356   0.1949   1.0000
  10.250   1.1998   0.04028   0.03116  -0.0333   0.1773   1.0000
  10.500   1.1972   0.04232   0.03327  -0.0311   0.1595   1.0000
  10.750   1.1915   0.04469   0.03562  -0.0294   0.1421   1.0000
  11.000   1.1849   0.04742   0.03831  -0.0283   0.1255   1.0000
  11.250   1.1791   0.05045   0.04140  -0.0276   0.1089   1.0000
  11.500   1.1732   0.05374   0.04473  -0.0272   0.0951   1.0000
  11.750   1.1672   0.05731   0.04837  -0.0270   0.0839   1.0000
  12.000   1.1606   0.06108   0.05209  -0.0271   0.0759   1.0000
  12.250   1.1560   0.06489   0.05606  -0.0272   0.0676   1.0000
  12.500   1.1507   0.06887   0.06011  -0.0275   0.0616   1.0000
  12.750   1.1463   0.07286   0.06422  -0.0280   0.0566   1.0000
  13.000   1.1421   0.07682   0.06818  -0.0285   0.0534   1.0000
  13.250   1.1408   0.08082   0.07248  -0.0288   0.0502   1.0000
  13.500   1.1384   0.08498   0.07685  -0.0294   0.0478   1.0000
  13.750   1.1357   0.08918   0.08119  -0.0302   0.0460   1.0000
  14.000   1.1341   0.09320   0.08529  -0.0309   0.0444   1.0000
  14.250   1.1306   0.09789   0.09014  -0.0321   0.0433   1.0000
  14.500   1.1207   0.10407   0.09663  -0.0346   0.0426   1.0000
  14.750   1.1084   0.11089   0.10373  -0.0378   0.0423   1.0000
  15.000   1.0933   0.11870   0.11178  -0.0419   0.0420   1.0000
  15.250   1.0760   0.12750   0.12079  -0.0469   0.0422   1.0000
  15.500   1.0571   0.13731   0.13076  -0.0527   0.0425   1.0000
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