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S4110 (s4110-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 100,000
Max Cl/Cd: 60.11 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4110-il-100000.txt
Download as CSV file: xf-s4110-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4110                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3110   0.10307   0.09825  -0.0321   1.0000   0.0883
  -9.250  -0.3256   0.10117   0.09645  -0.0348   1.0000   0.0890
  -9.000  -0.3389   0.09895   0.09432  -0.0370   1.0000   0.0893
  -8.750  -0.2990   0.09177   0.08706  -0.0314   1.0000   0.0931
  -8.500  -0.2954   0.08879   0.08412  -0.0310   1.0000   0.0969
  -8.250  -0.3033   0.08617   0.08158  -0.0319   1.0000   0.1012
  -8.000  -0.3202   0.08409   0.07962  -0.0334   1.0000   0.1026
  -7.750  -0.3414   0.08239   0.07805  -0.0339   1.0000   0.1030
  -7.500  -0.3110   0.07667   0.07230  -0.0302   1.0000   0.1077
  -7.250  -0.3139   0.07415   0.06984  -0.0288   1.0000   0.1110
  -7.000  -0.3280   0.07219   0.06799  -0.0272   1.0000   0.1139
  -6.750  -0.3496   0.07078   0.06671  -0.0250   1.0000   0.1152
  -6.500  -0.3758   0.06893   0.06495  -0.0276   1.0000   0.1168
  -6.250  -0.3965   0.06565   0.06161  -0.0342   1.0000   0.1176
  -6.000  -0.3832   0.06236   0.05850  -0.0243   1.0000   0.1205
  -5.750  -0.3833   0.05990   0.05607  -0.0221   1.0000   0.1234
  -5.500  -0.3867   0.05685   0.05303  -0.0235   1.0000   0.1281
  -5.250  -0.3895   0.05190   0.04797  -0.0295   1.0000   0.1340
  -5.000  -0.3844   0.04941   0.04554  -0.0267   1.0000   0.1368
  -4.750  -0.3752   0.04487   0.04079  -0.0328   1.0000   0.1482
  -4.500  -0.3313   0.03858   0.03267  -0.0513   1.0000   0.0778
  -4.250  -0.3058   0.03394   0.02757  -0.0524   1.0000   0.0697
  -4.000  -0.2756   0.02920   0.02201  -0.0540   1.0000   0.0663
  -3.750  -0.2495   0.02699   0.01938  -0.0542   1.0000   0.0690
  -3.500  -0.2226   0.02529   0.01706  -0.0542   1.0000   0.0745
  -3.250  -0.1966   0.02325   0.01480  -0.0542   1.0000   0.0802
  -3.000  -0.1710   0.02186   0.01311  -0.0539   1.0000   0.0914
  -2.750  -0.1482   0.02113   0.01238  -0.0535   1.0000   0.1095
  -2.500  -0.1253   0.02058   0.01172  -0.0531   1.0000   0.1294
  -2.250  -0.1022   0.01999   0.01104  -0.0526   1.0000   0.1459
  -2.000  -0.0793   0.01943   0.01050  -0.0521   1.0000   0.1616
  -1.750  -0.0422   0.01892   0.01016  -0.0544   0.9953   0.1875
  -1.500  -0.0020   0.01837   0.00985  -0.0571   0.9887   0.2308
  -1.250   0.0385   0.01726   0.00986  -0.0601   0.9836   0.4327
  -1.000   0.0685   0.01584   0.00995  -0.0590   0.9756   1.0000
  -0.750   0.1123   0.01627   0.01002  -0.0625   0.9675   1.0000
  -0.500   0.1554   0.01663   0.01009  -0.0659   0.9585   1.0000
  -0.250   0.1939   0.01692   0.01019  -0.0683   0.9485   1.0000
   0.000   0.2368   0.01721   0.01030  -0.0714   0.9396   1.0000
   0.250   0.2798   0.01742   0.01037  -0.0745   0.9301   1.0000
   0.500   0.3173   0.01760   0.01045  -0.0764   0.9188   1.0000
   0.750   0.3583   0.01772   0.01048  -0.0788   0.9086   1.0000
   1.000   0.4077   0.01766   0.01037  -0.0826   0.9003   1.0000
   1.250   0.4452   0.01767   0.01035  -0.0842   0.8883   1.0000
   1.500   0.4865   0.01756   0.01022  -0.0863   0.8770   1.0000
   1.750   0.5307   0.01729   0.00996  -0.0886   0.8669   1.0000
   2.000   0.5747   0.01689   0.00958  -0.0905   0.8566   1.0000
   2.250   0.6094   0.01665   0.00935  -0.0909   0.8431   1.0000
   2.500   0.6434   0.01636   0.00909  -0.0909   0.8290   1.0000
   2.750   0.6764   0.01604   0.00881  -0.0907   0.8140   1.0000
   3.000   0.7086   0.01570   0.00849  -0.0902   0.7982   1.0000
   3.250   0.7349   0.01555   0.00836  -0.0889   0.7782   1.0000
   3.500   0.7634   0.01530   0.00814  -0.0878   0.7580   1.0000
   3.750   0.7906   0.01511   0.00795  -0.0865   0.7356   1.0000
   4.000   0.8179   0.01493   0.00775  -0.0853   0.7114   1.0000
   4.250   0.8429   0.01487   0.00766  -0.0837   0.6829   1.0000
   4.500   0.8671   0.01488   0.00767  -0.0822   0.6507   1.0000
   4.750   0.8905   0.01499   0.00771  -0.0805   0.6140   1.0000
   5.000   0.9132   0.01520   0.00780  -0.0788   0.5724   1.0000
   5.250   0.9347   0.01555   0.00797  -0.0770   0.5259   1.0000
   5.500   0.9546   0.01608   0.00830  -0.0752   0.4749   1.0000
   5.750   0.9736   0.01680   0.00873  -0.0733   0.4231   1.0000
   6.000   0.9918   0.01765   0.00930  -0.0715   0.3732   1.0000
   6.250   1.0102   0.01862   0.01000  -0.0698   0.3296   1.0000
   6.500   1.0290   0.01965   0.01078  -0.0683   0.2927   1.0000
   6.750   1.0485   0.02073   0.01165  -0.0670   0.2623   1.0000
   7.000   1.0684   0.02176   0.01258  -0.0658   0.2355   1.0000
   7.250   1.0888   0.02283   0.01360  -0.0646   0.2127   1.0000
   7.500   1.1092   0.02394   0.01459  -0.0636   0.1930   1.0000
   7.750   1.1301   0.02517   0.01576  -0.0626   0.1756   1.0000
   8.000   1.1503   0.02635   0.01703  -0.0614   0.1591   1.0000
   8.250   1.1710   0.02768   0.01838  -0.0604   0.1445   1.0000
   8.500   1.1918   0.02915   0.01987  -0.0594   0.1316   1.0000
   8.750   1.2123   0.03067   0.02137  -0.0585   0.1197   1.0000
   9.000   1.2336   0.03229   0.02299  -0.0577   0.1096   1.0000
   9.250   1.2510   0.03389   0.02494  -0.0562   0.1003   1.0000
   9.500   1.2712   0.03608   0.02720  -0.0553   0.0928   1.0000
   9.750   1.2880   0.03774   0.02906  -0.0538   0.0856   1.0000
  10.000   1.3035   0.04024   0.03179  -0.0524   0.0796   1.0000
  10.250   1.3168   0.04236   0.03422  -0.0506   0.0744   1.0000
  10.500   1.3313   0.04518   0.03707  -0.0496   0.0694   1.0000
  10.750   1.3332   0.04791   0.04040  -0.0466   0.0662   1.0000
  11.000   1.3371   0.05094   0.04379  -0.0441   0.0634   1.0000
  11.250   1.3477   0.05314   0.04606  -0.0428   0.0601   1.0000
  11.500   1.3446   0.05741   0.05058  -0.0406   0.0580   1.0000
  11.750   1.3279   0.06049   0.05410  -0.0367   0.0572   1.0000
  12.000   1.3080   0.06393   0.05789  -0.0332   0.0568   1.0000
  12.250   1.2861   0.06786   0.06212  -0.0307   0.0565   1.0000
  12.500   1.2622   0.07244   0.06698  -0.0295   0.0565   1.0000
  12.750   1.2373   0.07771   0.07249  -0.0297   0.0567   1.0000
  13.000   1.2113   0.08379   0.07877  -0.0312   0.0570   1.0000
  13.250   1.1853   0.09069   0.08582  -0.0340   0.0575   1.0000
  13.500   1.1600   0.09846   0.09372  -0.0379   0.0580   1.0000
  13.750   1.0421   0.13244   0.12796  -0.0624   0.0712   1.0000
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