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S4053 (s4053-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 100,000
Max Cl/Cd: 58.91 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4053-il-100000.txt
Download as CSV file: xf-s4053-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4053                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3806   0.09396   0.08913  -0.0313   1.0000   0.0919
  -8.000  -0.3883   0.09159   0.08686  -0.0328   1.0000   0.0949
  -7.750  -0.4108   0.08999   0.08542  -0.0355   1.0000   0.0964
  -7.500  -0.4294   0.08746   0.08294  -0.0424   1.0000   0.0971
  -7.250  -0.4069   0.08276   0.07832  -0.0336   1.0000   0.1001
  -7.000  -0.4033   0.08014   0.07575  -0.0320   1.0000   0.1034
  -6.750  -0.4087   0.07736   0.07305  -0.0331   1.0000   0.1074
  -6.500  -0.4355   0.07535   0.07085  -0.0418   1.0000   0.1113
  -6.250  -0.4255   0.07096   0.06672  -0.0361   1.0000   0.1132
  -6.000  -0.4232   0.06883   0.06466  -0.0324   1.0000   0.1163
  -5.750  -0.4261   0.06655   0.06239  -0.0315   1.0000   0.1211
  -5.500  -0.4319   0.06308   0.05879  -0.0338   1.0000   0.1274
  -5.250  -0.4288   0.06096   0.05676  -0.0306   1.0000   0.1306
  -5.000  -0.4259   0.05791   0.05349  -0.0329   1.0000   0.1414
  -4.750  -0.4202   0.05564   0.05131  -0.0300   1.0000   0.1452
  -4.500  -0.4118   0.05279   0.04831  -0.0308   1.0000   0.1573
  -4.250  -0.3999   0.05028   0.04567  -0.0312   0.9997   0.1710
  -4.000  -0.3679   0.04733   0.04273  -0.0336   0.9941   0.1914
  -3.750  -0.3365   0.04461   0.03989  -0.0368   0.9873   0.2293
  -3.500  -0.2620   0.03191   0.02485  -0.0456   0.9850   0.0792
  -3.250  -0.2226   0.02859   0.02066  -0.0468   0.9796   0.0674
  -3.000  -0.1840   0.02611   0.01774  -0.0487   0.9743   0.0647
  -2.750  -0.1447   0.02433   0.01555  -0.0505   0.9691   0.0635
  -2.500  -0.1084   0.02302   0.01400  -0.0518   0.9623   0.0658
  -2.250  -0.0666   0.02183   0.01271  -0.0544   0.9577   0.0722
  -2.000  -0.0364   0.02092   0.01184  -0.0548   0.9494   0.0790
  -1.750   0.0042   0.01994   0.01088  -0.0571   0.9442   0.0985
  -1.500   0.0601   0.01617   0.01035  -0.0614   0.9448   1.0000
  -1.250   0.0926   0.01635   0.01016  -0.0626   0.9354   1.0000
  -1.000   0.1394   0.01650   0.00997  -0.0665   0.9300   1.0000
  -0.750   0.1684   0.01669   0.00993  -0.0671   0.9199   1.0000
  -0.500   0.2080   0.01683   0.00987  -0.0696   0.9129   1.0000
  -0.250   0.2446   0.01696   0.00981  -0.0715   0.9047   1.0000
   0.000   0.2804   0.01709   0.00981  -0.0732   0.8967   1.0000
   0.250   0.3227   0.01711   0.00971  -0.0760   0.8899   1.0000
   0.500   0.3550   0.01725   0.00975  -0.0769   0.8810   1.0000
   0.750   0.3973   0.01719   0.00961  -0.0795   0.8746   1.0000
   1.000   0.4253   0.01737   0.00974  -0.0795   0.8646   1.0000
   1.250   0.4693   0.01718   0.00951  -0.0822   0.8588   1.0000
   1.500   0.4944   0.01738   0.00967  -0.0815   0.8475   1.0000
   1.750   0.5234   0.01748   0.00976  -0.0815   0.8373   1.0000
   2.000   0.5624   0.01726   0.00955  -0.0829   0.8300   1.0000
   2.250   0.5872   0.01741   0.00970  -0.0820   0.8179   1.0000
   2.500   0.6135   0.01751   0.00982  -0.0813   0.8063   1.0000
   2.750   0.6419   0.01753   0.00988  -0.0808   0.7953   1.0000
   3.000   0.6731   0.01741   0.00977  -0.0806   0.7849   1.0000
   3.250   0.7012   0.01736   0.00974  -0.0799   0.7727   1.0000
   3.500   0.7266   0.01738   0.00980  -0.0788   0.7590   1.0000
   3.750   0.7525   0.01736   0.00984  -0.0776   0.7449   1.0000
   4.000   0.7787   0.01731   0.00983  -0.0765   0.7303   1.0000
   4.250   0.8051   0.01722   0.00978  -0.0754   0.7150   1.0000
   4.500   0.8289   0.01721   0.00982  -0.0739   0.6974   1.0000
   4.750   0.8527   0.01714   0.00984  -0.0723   0.6780   1.0000
   5.000   0.8788   0.01694   0.00966  -0.0709   0.6584   1.0000
   5.250   0.9013   0.01687   0.00966  -0.0692   0.6353   1.0000
   5.500   0.9249   0.01673   0.00955  -0.0675   0.6106   1.0000
   5.750   0.9466   0.01665   0.00954  -0.0656   0.5817   1.0000
   6.000   0.9670   0.01664   0.00954  -0.0635   0.5475   1.0000
   6.250   0.9862   0.01674   0.00960  -0.0612   0.5065   1.0000
   6.500   1.0033   0.01704   0.00975  -0.0587   0.4574   1.0000
   6.750   1.0172   0.01765   0.01013  -0.0560   0.3969   1.0000
   7.000   1.0279   0.01865   0.01078  -0.0530   0.3310   1.0000
   7.250   1.0366   0.01996   0.01169  -0.0499   0.2672   1.0000
   7.500   1.0450   0.02151   0.01281  -0.0470   0.2168   1.0000
   7.750   1.0561   0.02306   0.01410  -0.0445   0.1794   1.0000
   8.000   1.0692   0.02457   0.01543  -0.0424   0.1530   1.0000
   8.250   1.0851   0.02619   0.01685  -0.0407   0.1346   1.0000
   8.500   1.1043   0.02789   0.01850  -0.0395   0.1196   1.0000
   8.750   1.1247   0.02964   0.02019  -0.0386   0.1066   1.0000
   9.000   1.1438   0.03118   0.02186  -0.0374   0.0959   1.0000
   9.250   1.1621   0.03299   0.02385  -0.0361   0.0858   1.0000
   9.500   1.1809   0.03516   0.02614  -0.0350   0.0765   1.0000
   9.750   1.2021   0.03793   0.02889  -0.0346   0.0683   1.0000
  10.000   1.2129   0.03973   0.03114  -0.0321   0.0622   1.0000
  10.250   1.2327   0.04311   0.03455  -0.0317   0.0574   1.0000
  10.500   1.2367   0.04612   0.03810  -0.0287   0.0546   1.0000
  10.750   1.2385   0.04882   0.04125  -0.0258   0.0517   1.0000
  11.000   1.2422   0.05155   0.04425  -0.0234   0.0492   1.0000
  11.250   1.2432   0.05483   0.04781  -0.0211   0.0481   1.0000
  11.500   1.2375   0.05821   0.05145  -0.0182   0.0474   1.0000
  11.750   1.2259   0.06169   0.05522  -0.0151   0.0471   1.0000
  12.000   1.2094   0.06531   0.05912  -0.0123   0.0471   1.0000
  12.250   1.1865   0.06932   0.06346  -0.0102   0.0475   1.0000
  12.500   1.1480   0.07463   0.06916  -0.0096   0.0486   1.0000
  12.750   1.1126   0.08105   0.07588  -0.0111   0.0498   1.0000
  13.000   1.0790   0.08842   0.08348  -0.0144   0.0510   1.0000
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