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S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S8052 (11.88%) (s8052-il)
Reynolds number: 50,000
Max Cl/Cd: 30.98 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8052-il-50000.txt
Download as CSV file: xf-s8052-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8052 (11.88%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4216   0.09994   0.09326  -0.0090   1.0000   0.3195
  -8.500  -0.4101   0.09591   0.08925  -0.0093   1.0000   0.3243
  -8.250  -0.5440   0.07591   0.06950  -0.0390   1.0000   0.1514
  -8.000  -0.5543   0.06930   0.06282  -0.0407   1.0000   0.1350
  -7.750  -0.5828   0.06333   0.05654  -0.0412   1.0000   0.1220
  -7.500  -0.5803   0.05964   0.05284  -0.0398   1.0000   0.1193
  -7.250  -0.5869   0.05609   0.04914  -0.0377   1.0000   0.1167
  -7.000  -0.5973   0.05254   0.04526  -0.0348   1.0000   0.1134
  -6.750  -0.6103   0.04949   0.04139  -0.0310   1.0000   0.1087
  -6.500  -0.6072   0.04668   0.03827  -0.0284   1.0000   0.1085
  -6.250  -0.6004   0.04393   0.03523  -0.0260   1.0000   0.1082
  -6.000  -0.5911   0.04123   0.03219  -0.0237   1.0000   0.1080
  -5.750  -0.5790   0.03867   0.02924  -0.0217   1.0000   0.1081
  -5.500  -0.5643   0.03636   0.02646  -0.0197   1.0000   0.1090
  -5.250  -0.5469   0.03392   0.02397  -0.0183   1.0000   0.1122
  -5.000  -0.5289   0.03225   0.02215  -0.0167   1.0000   0.1189
  -4.750  -0.5097   0.03048   0.02021  -0.0152   1.0000   0.1280
  -4.500  -0.4888   0.02884   0.01849  -0.0137   1.0000   0.1412
  -4.250  -0.4685   0.02737   0.01706  -0.0122   1.0000   0.1656
  -4.000  -0.4500   0.02564   0.01571  -0.0104   1.0000   0.2133
  -3.750  -0.4363   0.02298   0.01421  -0.0081   1.0000   0.3472
  -3.500  -0.4383   0.02141   0.01460  -0.0005   1.0000   0.5993
  -3.250  -0.4386   0.02203   0.01546   0.0081   1.0000   0.7274
  -3.000  -0.4363   0.02266   0.01609   0.0163   1.0000   0.8031
  -2.750  -0.4151   0.02358   0.01684   0.0220   1.0000   0.8756
  -2.500  -0.1347   0.02617   0.01783  -0.0167   1.0000   0.9844
  -2.250  -0.0838   0.02560   0.01694  -0.0238   1.0000   1.0000
  -2.000  -0.0917   0.02534   0.01661  -0.0206   1.0000   1.0000
  -1.750  -0.0991   0.02508   0.01626  -0.0173   1.0000   1.0000
  -1.500  -0.1061   0.02481   0.01592  -0.0139   1.0000   1.0000
  -1.250  -0.1131   0.02453   0.01556  -0.0104   1.0000   1.0000
  -1.000  -0.1201   0.02422   0.01519  -0.0069   1.0000   1.0000
  -0.750  -0.1261   0.02393   0.01480  -0.0033   1.0000   1.0000
  -0.500  -0.1288   0.02371   0.01448  -0.0003   1.0000   1.0000
  -0.250  -0.1262   0.02365   0.01428   0.0021   1.0000   1.0000
   0.000  -0.1177   0.02377   0.01425   0.0035   1.0000   1.0000
   0.250  -0.1055   0.02404   0.01437   0.0044   1.0000   1.0000
   0.500  -0.0882   0.02447   0.01466   0.0044   0.9988   1.0000
   0.750  -0.0395   0.02574   0.01578  -0.0014   0.9853   1.0000
   1.000   0.0064   0.02695   0.01687  -0.0064   0.9716   1.0000
   1.250   0.0511   0.02811   0.01793  -0.0111   0.9569   1.0000
   1.500   0.0948   0.02923   0.01899  -0.0155   0.9416   1.0000
   1.750   0.1340   0.03021   0.01992  -0.0188   0.9250   1.0000
   2.000   0.1702   0.03113   0.02081  -0.0215   0.9075   1.0000
   2.250   0.2078   0.03204   0.02172  -0.0241   0.8889   1.0000
   2.500   0.2501   0.03294   0.02263  -0.0273   0.8698   1.0000
   2.750   0.2974   0.03378   0.02351  -0.0309   0.8505   1.0000
   3.000   0.3256   0.03445   0.02423  -0.0314   0.8290   1.0000
   3.250   0.3729   0.03497   0.02483  -0.0343   0.8079   1.0000
   3.500   0.4091   0.03543   0.02536  -0.0354   0.7857   1.0000
   3.750   0.4562   0.03551   0.02558  -0.0374   0.7631   1.0000
   4.000   0.4999   0.03543   0.02563  -0.0386   0.7403   1.0000
   4.250   0.5439   0.03494   0.02531  -0.0391   0.7175   1.0000
   4.500   0.5826   0.03432   0.02482  -0.0385   0.6943   1.0000
   4.750   0.6257   0.03314   0.02377  -0.0377   0.6713   1.0000
   5.000   0.6574   0.03231   0.02308  -0.0358   0.6457   1.0000
   5.250   0.6990   0.03068   0.02156  -0.0342   0.6211   1.0000
   5.500   0.7384   0.02902   0.01996  -0.0323   0.5940   1.0000
   5.750   0.7672   0.02812   0.01908  -0.0299   0.5618   1.0000
   6.000   0.7957   0.02750   0.01839  -0.0277   0.5274   1.0000
   6.250   0.8245   0.02715   0.01788  -0.0257   0.4925   1.0000
   6.500   0.8497   0.02743   0.01797  -0.0239   0.4585   1.0000
   6.750   0.8709   0.02815   0.01856  -0.0222   0.4262   1.0000
   7.000   0.8933   0.02903   0.01928  -0.0207   0.3972   1.0000
   7.250   0.9165   0.02998   0.02008  -0.0195   0.3705   1.0000
   7.500   0.9343   0.03131   0.02147  -0.0179   0.3461   1.0000
   7.750   0.9576   0.03257   0.02258  -0.0169   0.3239   1.0000
   8.000   0.9746   0.03412   0.02425  -0.0155   0.3032   1.0000
   8.250   0.9952   0.03562   0.02574  -0.0144   0.2838   1.0000
   8.500   1.0180   0.03724   0.02725  -0.0135   0.2659   1.0000
   8.750   1.0339   0.03913   0.02928  -0.0121   0.2498   1.0000
   9.000   1.0517   0.04117   0.03139  -0.0109   0.2355   1.0000
   9.250   1.0675   0.04318   0.03352  -0.0096   0.2220   1.0000
   9.500   1.0703   0.04607   0.03689  -0.0074   0.2127   1.0000
   9.750   1.0826   0.04877   0.03976  -0.0060   0.2037   1.0000
  10.000   1.0965   0.05109   0.04219  -0.0048   0.1940   1.0000
  10.250   1.0901   0.05470   0.04620  -0.0025   0.1889   1.0000
  10.500   1.0755   0.05876   0.05066   0.0000   0.1855   1.0000
  10.750   1.0576   0.06312   0.05530   0.0021   0.1837   1.0000
  11.000   1.0202   0.06829   0.06069   0.0045   0.1845   1.0000
  11.250   0.9642   0.07575   0.06822   0.0043   0.1880   1.0000
  11.500   0.9180   0.08496   0.07745   0.0009   0.1907   1.0000
  11.750   0.8867   0.09445   0.08692  -0.0033   0.1922   1.0000
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