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S4110 (s4110-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 200,000
Max Cl/Cd: 73.55 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4110-il-200000-n5.txt
Download as CSV file: xf-s4110-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4093   0.08864   0.08495  -0.0338   1.0000   0.0167
  -8.750  -0.4099   0.08543   0.08179  -0.0344   1.0000   0.0165
  -8.500  -0.4124   0.08215   0.07855  -0.0350   1.0000   0.0164
  -8.250  -0.4194   0.07854   0.07501  -0.0355   1.0000   0.0163
  -8.000  -0.4288   0.07562   0.07218  -0.0351   1.0000   0.0162
  -7.750  -0.4403   0.07244   0.06909  -0.0351   1.0000   0.0160
  -7.500  -0.4492   0.06860   0.06531  -0.0366   1.0000   0.0159
  -7.250  -0.4578   0.06420   0.06094  -0.0388   1.0000   0.0157
  -7.000  -0.4359   0.05085   0.04738  -0.0562   0.9926   0.0154
  -6.750  -0.4163   0.02998   0.02514  -0.0733   0.9837   0.0150
  -6.500  -0.3902   0.02517   0.01953  -0.0758   0.9780   0.0153
  -6.250  -0.3595   0.02232   0.01613  -0.0777   0.9740   0.0158
  -6.000  -0.3264   0.02036   0.01374  -0.0795   0.9711   0.0165
  -5.750  -0.2975   0.01907   0.01225  -0.0803   0.9660   0.0177
  -5.500  -0.2660   0.01817   0.01124  -0.0814   0.9617   0.0189
  -5.250  -0.2323   0.01706   0.00992  -0.0828   0.9586   0.0200
  -5.000  -0.1996   0.01607   0.00876  -0.0839   0.9550   0.0211
  -4.750  -0.1697   0.01524   0.00779  -0.0844   0.9493   0.0225
  -4.250  -0.1024   0.01387   0.00626  -0.0869   0.9420   0.0300
  -4.000  -0.0737   0.01343   0.00583  -0.0871   0.9352   0.0397
  -3.750  -0.0405   0.01303   0.00542  -0.0882   0.9307   0.0513
  -3.500  -0.0091   0.01276   0.00512  -0.0888   0.9252   0.0623
  -3.250   0.0214   0.01249   0.00485  -0.0894   0.9187   0.0763
  -3.000   0.0547   0.01214   0.00450  -0.0904   0.9142   0.0882
  -2.750   0.0828   0.01183   0.00420  -0.0904   0.9060   0.0989
  -2.500   0.1148   0.01152   0.00389  -0.0912   0.9004   0.1152
  -2.250   0.1431   0.01125   0.00368  -0.0912   0.8922   0.1375
  -2.000   0.1739   0.01094   0.00345  -0.0917   0.8857   0.1706
  -1.750   0.2014   0.01063   0.00331  -0.0916   0.8766   0.2226
  -1.500   0.2306   0.01026   0.00317  -0.0919   0.8691   0.3012
  -1.250   0.2575   0.00990   0.00310  -0.0917   0.8595   0.3948
  -1.000   0.2841   0.00956   0.00306  -0.0914   0.8501   0.4966
  -0.750   0.3106   0.00923   0.00302  -0.0908   0.8412   0.5979
  -0.500   0.3339   0.00892   0.00303  -0.0894   0.8300   0.7023
   0.000   0.3898   0.00838   0.00289  -0.0877   0.8082   0.9498
   0.250   0.4229   0.00837   0.00278  -0.0886   0.7964   1.0000
   0.500   0.4500   0.00843   0.00272  -0.0882   0.7834   1.0000
   0.750   0.4768   0.00849   0.00269  -0.0878   0.7691   1.0000
   1.000   0.5034   0.00857   0.00267  -0.0873   0.7539   1.0000
   1.250   0.5300   0.00865   0.00267  -0.0868   0.7379   1.0000
   1.500   0.5565   0.00874   0.00268  -0.0863   0.7208   1.0000
   1.750   0.5828   0.00885   0.00270  -0.0858   0.7022   1.0000
   2.250   0.6350   0.00912   0.00278  -0.0847   0.6596   1.0000
   2.500   0.6606   0.00929   0.00285  -0.0840   0.6352   1.0000
   2.750   0.6858   0.00949   0.00292  -0.0833   0.6075   1.0000
   3.000   0.7107   0.00972   0.00302  -0.0825   0.5769   1.0000
   3.250   0.7351   0.01000   0.00315  -0.0817   0.5436   1.0000
   3.500   0.7590   0.01032   0.00333  -0.0809   0.5087   1.0000
   3.750   0.7828   0.01066   0.00352  -0.0800   0.4730   1.0000
   4.000   0.8061   0.01105   0.00374  -0.0792   0.4362   1.0000
   4.250   0.8293   0.01147   0.00400  -0.0783   0.3986   1.0000
   4.500   0.8523   0.01193   0.00431  -0.0775   0.3628   1.0000
   4.750   0.8753   0.01239   0.00463  -0.0767   0.3282   1.0000
   5.000   0.8982   0.01288   0.00498  -0.0759   0.2954   1.0000
   5.250   0.9211   0.01337   0.00535  -0.0751   0.2660   1.0000
   5.500   0.9440   0.01387   0.00576  -0.0743   0.2385   1.0000
   5.750   0.9668   0.01438   0.00618  -0.0736   0.2142   1.0000
   6.000   0.9895   0.01491   0.00662  -0.0728   0.1923   1.0000
   6.250   1.0123   0.01542   0.00707  -0.0721   0.1722   1.0000
   6.500   1.0349   0.01595   0.00755  -0.0713   0.1549   1.0000
   6.750   1.0574   0.01649   0.00808  -0.0705   0.1398   1.0000
   7.000   1.0797   0.01703   0.00861  -0.0697   0.1267   1.0000
   7.250   1.1018   0.01759   0.00916  -0.0689   0.1148   1.0000
   7.500   1.1236   0.01817   0.00974  -0.0680   0.1046   1.0000
   7.750   1.1447   0.01880   0.01038  -0.0671   0.0949   1.0000
   8.000   1.1661   0.01938   0.01101  -0.0662   0.0855   1.0000
   8.250   1.1870   0.02001   0.01168  -0.0652   0.0773   1.0000
   8.500   1.2065   0.02074   0.01241  -0.0641   0.0696   1.0000
   8.750   1.2268   0.02140   0.01314  -0.0630   0.0623   1.0000
   9.000   1.2453   0.02219   0.01399  -0.0618   0.0565   1.0000
   9.250   1.2639   0.02295   0.01482  -0.0606   0.0509   1.0000
   9.500   1.2805   0.02384   0.01575  -0.0591   0.0460   1.0000
   9.750   1.2978   0.02465   0.01667  -0.0577   0.0416   1.0000
  10.000   1.3114   0.02572   0.01775  -0.0560   0.0377   1.0000
  10.250   1.3262   0.02657   0.01874  -0.0542   0.0347   1.0000
  10.500   1.3389   0.02752   0.01979  -0.0522   0.0318   1.0000
  10.750   1.3474   0.02875   0.02108  -0.0499   0.0292   1.0000
  11.000   1.3576   0.02988   0.02236  -0.0478   0.0272   1.0000
  11.250   1.3670   0.03109   0.02371  -0.0458   0.0253   1.0000
  11.500   1.3748   0.03242   0.02516  -0.0437   0.0237   1.0000
  11.750   1.3793   0.03402   0.02686  -0.0416   0.0224   1.0000
  12.000   1.3807   0.03599   0.02893  -0.0395   0.0213   1.0000
  12.250   1.3863   0.03769   0.03082  -0.0378   0.0202   1.0000
  12.500   1.3904   0.03957   0.03287  -0.0363   0.0190   1.0000
  12.750   1.3932   0.04160   0.03505  -0.0351   0.0180   1.0000
  13.000   1.3947   0.04384   0.03743  -0.0341   0.0171   1.0000
  13.250   1.3926   0.04657   0.04031  -0.0332   0.0165   1.0000
  13.500   1.3868   0.04989   0.04375  -0.0327   0.0160   1.0000
  13.750   1.3816   0.05337   0.04740  -0.0325   0.0156   1.0000
  14.000   1.3771   0.05697   0.05122  -0.0327   0.0152   1.0000
  14.250   1.3710   0.06097   0.05542  -0.0333   0.0149   1.0000
  14.500   1.3631   0.06542   0.06007  -0.0344   0.0146   1.0000
  14.750   1.3538   0.07034   0.06520  -0.0360   0.0143   1.0000
  15.000   1.3432   0.07574   0.07079  -0.0382   0.0140   1.0000
  15.250   1.3311   0.08171   0.07696  -0.0409   0.0139   1.0000
  15.500   1.3181   0.08819   0.08363  -0.0442   0.0137   1.0000
  15.750   1.3034   0.09531   0.09094  -0.0480   0.0135   1.0000
  16.000   1.2876   0.10305   0.09887  -0.0524   0.0134   1.0000
  16.250   1.2701   0.11145   0.10746  -0.0573   0.0134   1.0000
  16.500   1.2513   0.12054   0.11672  -0.0628   0.0134   1.0000
  16.750   1.2302   0.13057   0.12694  -0.0689   0.0135   1.0000
  17.000   1.2060   0.14187   0.13842  -0.0760   0.0137   1.0000
  17.250   1.1751   0.15576   0.15249  -0.0847   0.0140   1.0000
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