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S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S8052 (11.88%) (s8052-il)
Reynolds number: 50,000
Max Cl/Cd: 32.42 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8052-il-50000-n5.txt
Download as CSV file: xf-s8052-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3886   0.12318   0.11633  -0.0189   1.0000   0.0515
 -11.750  -0.3894   0.11902   0.11219  -0.0206   1.0000   0.0504
 -11.250  -0.5098   0.11109   0.10380  -0.0237   1.0000   0.0453
 -11.000  -0.5079   0.10663   0.09939  -0.0254   1.0000   0.0450
 -10.750  -0.5080   0.10178   0.09458  -0.0275   1.0000   0.0446
 -10.500  -0.5095   0.09671   0.08956  -0.0300   1.0000   0.0442
 -10.250  -0.5143   0.09074   0.08365  -0.0334   1.0000   0.0438
 -10.000  -0.5227   0.08410   0.07705  -0.0378   1.0000   0.0432
  -9.750  -0.5376   0.07746   0.07041  -0.0425   1.0000   0.0426
  -9.500  -0.5566   0.07170   0.06463  -0.0463   1.0000   0.0421
  -9.250  -0.5763   0.06713   0.06001  -0.0478   1.0000   0.0418
  -9.000  -0.5939   0.06324   0.05601  -0.0475   1.0000   0.0415
  -8.750  -0.6055   0.05946   0.05205  -0.0469   1.0000   0.0413
  -8.500  -0.6134   0.05580   0.04816  -0.0458   1.0000   0.0412
  -8.250  -0.6173   0.05240   0.04449  -0.0443   1.0000   0.0412
  -8.000  -0.6183   0.04930   0.04109  -0.0424   1.0000   0.0417
  -7.750  -0.6170   0.04654   0.03801  -0.0402   1.0000   0.0423
  -7.500  -0.6142   0.04409   0.03524  -0.0376   1.0000   0.0431
  -7.250  -0.6106   0.04179   0.03254  -0.0348   1.0000   0.0443
  -7.000  -0.6050   0.03975   0.03010  -0.0320   1.0000   0.0455
  -6.750  -0.5968   0.03791   0.02819  -0.0297   1.0000   0.0468
  -6.500  -0.5870   0.03629   0.02643  -0.0274   1.0000   0.0482
  -6.250  -0.5751   0.03472   0.02467  -0.0251   1.0000   0.0495
  -6.000  -0.5615   0.03323   0.02294  -0.0230   1.0000   0.0513
  -5.750  -0.5465   0.03185   0.02135  -0.0210   1.0000   0.0536
  -5.500  -0.5313   0.03062   0.01994  -0.0190   1.0000   0.0572
  -5.250  -0.5044   0.02937   0.01867  -0.0194   0.9951   0.0639
  -5.000  -0.4742   0.02806   0.01727  -0.0203   0.9886   0.0728
  -4.750  -0.4437   0.02681   0.01599  -0.0214   0.9824   0.0903
  -4.500  -0.4165   0.02548   0.01480  -0.0220   0.9753   0.1235
  -4.250  -0.3886   0.02386   0.01371  -0.0233   0.9691   0.1974
  -4.000  -0.3667   0.02239   0.01301  -0.0236   0.9616   0.3232
  -3.750  -0.3435   0.02144   0.01294  -0.0229   0.9554   0.4832
  -3.500  -0.3232   0.02143   0.01333  -0.0203   0.9477   0.6029
  -3.250  -0.2946   0.02172   0.01358  -0.0192   0.9418   0.6817
  -3.000  -0.2726   0.02199   0.01376  -0.0171   0.9341   0.7307
  -2.750  -0.2425   0.02228   0.01387  -0.0163   0.9282   0.7725
  -2.500  -0.2159   0.02252   0.01396  -0.0151   0.9214   0.8057
  -2.250  -0.1825   0.02276   0.01402  -0.0152   0.9155   0.8357
  -2.000  -0.1370   0.02300   0.01404  -0.0176   0.9117   0.8615
  -1.750  -0.1008   0.02317   0.01402  -0.0188   0.9048   0.8836
  -1.500  -0.0496   0.02331   0.01395  -0.0229   0.9002   0.9021
  -1.250   0.0068   0.02339   0.01382  -0.0282   0.8965   0.9176
  -1.000   0.0524   0.02345   0.01372  -0.0319   0.8894   0.9320
  -0.750   0.1061   0.02342   0.01355  -0.0371   0.8841   0.9439
  -0.500   0.1529   0.02340   0.01341  -0.0412   0.8773   0.9561
  -0.250   0.2023   0.02331   0.01323  -0.0458   0.8701   0.9662
   0.000   0.2479   0.02322   0.01307  -0.0497   0.8624   0.9764
   0.250   0.2921   0.02310   0.01291  -0.0533   0.8539   0.9863
   0.500   0.3334   0.02302   0.01281  -0.0565   0.8443   0.9966
   0.750   0.3656   0.02293   0.01269  -0.0577   0.8348   1.0000
   1.000   0.3824   0.02302   0.01276  -0.0562   0.8226   1.0000
   1.250   0.3969   0.02313   0.01287  -0.0542   0.8097   1.0000
   1.500   0.4121   0.02323   0.01297  -0.0522   0.7968   1.0000
   1.750   0.4285   0.02329   0.01303  -0.0502   0.7841   1.0000
   2.000   0.4464   0.02331   0.01305  -0.0484   0.7714   1.0000
   2.250   0.4660   0.02326   0.01299  -0.0466   0.7587   1.0000
   2.500   0.4838   0.02326   0.01299  -0.0445   0.7450   1.0000
   2.750   0.5007   0.02328   0.01304  -0.0423   0.7302   1.0000
   3.000   0.5188   0.02328   0.01303  -0.0402   0.7151   1.0000
   3.250   0.5380   0.02324   0.01300  -0.0382   0.6997   1.0000
   3.500   0.5584   0.02316   0.01295  -0.0362   0.6836   1.0000
   3.750   0.5752   0.02323   0.01306  -0.0340   0.6649   1.0000
   4.000   0.5944   0.02321   0.01308  -0.0321   0.6457   1.0000
   4.250   0.6161   0.02309   0.01298  -0.0303   0.6261   1.0000
   4.500   0.6361   0.02305   0.01299  -0.0284   0.6039   1.0000
   4.750   0.6586   0.02291   0.01288  -0.0267   0.5808   1.0000
   5.000   0.6799   0.02289   0.01287  -0.0250   0.5546   1.0000
   5.250   0.7022   0.02289   0.01283  -0.0234   0.5264   1.0000
   5.500   0.7241   0.02299   0.01289  -0.0217   0.4960   1.0000
   5.750   0.7452   0.02323   0.01302  -0.0201   0.4646   1.0000
   6.000   0.7650   0.02362   0.01327  -0.0185   0.4324   1.0000
   6.250   0.7839   0.02418   0.01369  -0.0169   0.4016   1.0000
   6.500   0.8018   0.02485   0.01425  -0.0153   0.3724   1.0000
   6.750   0.8193   0.02561   0.01492  -0.0138   0.3455   1.0000
   7.000   0.8367   0.02644   0.01563  -0.0124   0.3216   1.0000
   7.250   0.8539   0.02731   0.01643  -0.0110   0.2992   1.0000
   7.500   0.8714   0.02822   0.01728  -0.0098   0.2796   1.0000
   7.750   0.8886   0.02917   0.01824  -0.0085   0.2605   1.0000
   8.000   0.9062   0.03015   0.01922  -0.0074   0.2437   1.0000
   8.250   0.9236   0.03117   0.02025  -0.0062   0.2279   1.0000
   8.500   0.9414   0.03223   0.02137  -0.0052   0.2135   1.0000
   8.750   0.9583   0.03333   0.02251  -0.0041   0.1997   1.0000
   9.000   0.9751   0.03449   0.02371  -0.0030   0.1872   1.0000
   9.250   0.9917   0.03568   0.02491  -0.0019   0.1757   1.0000
   9.500   1.0066   0.03691   0.02619  -0.0007   0.1646   1.0000
   9.750   1.0213   0.03832   0.02779   0.0005   0.1543   1.0000
  10.000   1.0353   0.03973   0.02929   0.0016   0.1452   1.0000
  10.250   1.0481   0.04110   0.03073   0.0029   0.1371   1.0000
  10.500   1.0602   0.04284   0.03269   0.0042   0.1298   1.0000
  10.750   1.0717   0.04436   0.03426   0.0055   0.1234   1.0000
  11.000   1.0794   0.04629   0.03640   0.0069   0.1175   1.0000
  11.250   1.0858   0.04823   0.03853   0.0083   0.1121   1.0000
  11.500   1.1016   0.04990   0.04017   0.0090   0.1078   1.0000
  11.750   1.0981   0.05282   0.04352   0.0106   0.1043   1.0000
  12.000   1.0957   0.05560   0.04656   0.0117   0.1008   1.0000
  12.250   1.0984   0.05787   0.04895   0.0125   0.0974   1.0000
  12.500   1.1044   0.06008   0.05118   0.0131   0.0944   1.0000
  12.750   1.0868   0.06445   0.05592   0.0134   0.0927   1.0000
  13.000   1.0665   0.06944   0.06122   0.0128   0.0915   1.0000
  13.250   1.0413   0.07546   0.06751   0.0112   0.0907   1.0000
  13.500   1.0063   0.08347   0.07575   0.0076   0.0905   1.0000
  13.750   0.9521   0.09609   0.08855   0.0003   0.0913   1.0000
  14.000   0.8813   0.11591   0.10836  -0.0119   0.0923   1.0000
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