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S2091-101-83 (s2091-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 100,000
Max Cl/Cd: 57.92 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2091-il-100000-n5.txt
Download as CSV file: xf-s2091-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2091-101-83                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3352   0.09656   0.09170  -0.0347   1.0000   0.0347
  -8.750  -0.3255   0.09380   0.08897  -0.0342   1.0000   0.0340
  -8.250  -0.3196   0.08720   0.08248  -0.0361   1.0000   0.0325
  -8.000  -0.3206   0.08396   0.07933  -0.0371   1.0000   0.0319
  -7.750  -0.3276   0.08092   0.07641  -0.0375   1.0000   0.0313
  -7.500  -0.3446   0.07898   0.07462  -0.0357   1.0000   0.0309
  -7.000  -0.3225   0.05694   0.05240  -0.0656   0.9719   0.0284
  -6.750  -0.3023   0.04845   0.04359  -0.0752   0.9599   0.0286
  -6.500  -0.2745   0.04826   0.04342  -0.0768   0.9516   0.0304
  -6.250  -0.2507   0.04141   0.03608  -0.0835   0.9417   0.0317
  -6.000  -0.2288   0.03514   0.02910  -0.0875   0.9311   0.0329
  -5.750  -0.2056   0.03026   0.02338  -0.0894   0.9211   0.0340
  -5.500  -0.1772   0.02795   0.02068  -0.0907   0.9139   0.0363
  -5.250  -0.1520   0.02671   0.01922  -0.0907   0.9041   0.0390
  -5.000  -0.1234   0.02451   0.01647  -0.0911   0.8970   0.0414
  -4.750  -0.0976   0.02322   0.01494  -0.0909   0.8876   0.0445
  -4.500  -0.0700   0.02228   0.01382  -0.0909   0.8798   0.0481
  -4.250  -0.0431   0.02110   0.01233  -0.0904   0.8711   0.0515
  -4.000  -0.0167   0.02027   0.01146  -0.0902   0.8629   0.0560
  -3.750   0.0101   0.01949   0.01053  -0.0897   0.8546   0.0612
  -3.500   0.0361   0.01874   0.00973  -0.0892   0.8459   0.0670
  -3.250   0.0630   0.01819   0.00905  -0.0887   0.8379   0.0760
  -3.000   0.0886   0.01763   0.00851  -0.0882   0.8288   0.0861
  -2.750   0.1154   0.01714   0.00799  -0.0877   0.8211   0.1000
  -2.500   0.1412   0.01675   0.00759  -0.0872   0.8115   0.1174
  -2.250   0.1679   0.01629   0.00716  -0.0867   0.8042   0.1397
  -2.000   0.1937   0.01591   0.00687  -0.0863   0.7942   0.1705
  -1.750   0.2201   0.01546   0.00658  -0.0859   0.7860   0.2220
  -1.500   0.2460   0.01501   0.00639  -0.0855   0.7768   0.3071
  -1.250   0.2711   0.01454   0.00629  -0.0848   0.7677   0.4267
  -1.000   0.2954   0.01406   0.00621  -0.0837   0.7593   0.5640
  -0.750   0.3163   0.01360   0.00619  -0.0816   0.7495   0.7110
  -0.500   0.3572   0.01298   0.00586  -0.0827   0.7416   1.0000
  -0.250   0.3837   0.01307   0.00576  -0.0823   0.7308   1.0000
   0.000   0.4104   0.01315   0.00565  -0.0819   0.7209   1.0000
   0.250   0.4374   0.01320   0.00552  -0.0814   0.7117   1.0000
   0.500   0.4640   0.01331   0.00550  -0.0811   0.7004   1.0000
   0.750   0.4908   0.01341   0.00546  -0.0807   0.6901   1.0000
   1.000   0.5178   0.01349   0.00538  -0.0802   0.6804   1.0000
   1.250   0.5443   0.01362   0.00542  -0.0798   0.6686   1.0000
   1.500   0.5710   0.01374   0.00544  -0.0794   0.6573   1.0000
   1.750   0.5978   0.01385   0.00544  -0.0790   0.6464   1.0000
   2.000   0.6245   0.01397   0.00547  -0.0786   0.6351   1.0000
   2.250   0.6509   0.01413   0.00556  -0.0782   0.6226   1.0000
   2.500   0.6774   0.01428   0.00565  -0.0778   0.6102   1.0000
   2.750   0.7039   0.01444   0.00573  -0.0773   0.5982   1.0000
   3.000   0.7303   0.01461   0.00583  -0.0769   0.5860   1.0000
   3.250   0.7566   0.01479   0.00595  -0.0764   0.5734   1.0000
   3.500   0.7826   0.01499   0.00611  -0.0760   0.5598   1.0000
   3.750   0.8086   0.01520   0.00629  -0.0756   0.5463   1.0000
   4.000   0.8344   0.01543   0.00650  -0.0751   0.5326   1.0000
   4.250   0.8601   0.01567   0.00671  -0.0747   0.5187   1.0000
   4.500   0.8856   0.01592   0.00693  -0.0742   0.5047   1.0000
   4.750   0.9109   0.01620   0.00719  -0.0737   0.4905   1.0000
   5.000   0.9361   0.01649   0.00746  -0.0731   0.4761   1.0000
   5.250   0.9609   0.01680   0.00775  -0.0726   0.4616   1.0000
   5.500   0.9855   0.01713   0.00809  -0.0720   0.4469   1.0000
   5.750   1.0099   0.01749   0.00843  -0.0715   0.4322   1.0000
   6.000   1.0339   0.01786   0.00880  -0.0708   0.4172   1.0000
   6.250   1.0577   0.01826   0.00922  -0.0702   0.4023   1.0000
   6.500   1.0810   0.01869   0.00965  -0.0695   0.3873   1.0000
   6.750   1.1040   0.01914   0.01011  -0.0688   0.3722   1.0000
   7.000   1.1266   0.01961   0.01060  -0.0681   0.3571   1.0000
   7.250   1.1486   0.02012   0.01113  -0.0673   0.3421   1.0000
   7.500   1.1702   0.02065   0.01169  -0.0664   0.3269   1.0000
   7.750   1.1911   0.02121   0.01227  -0.0656   0.3119   1.0000
   8.000   1.2115   0.02181   0.01290  -0.0646   0.2969   1.0000
   8.250   1.2311   0.02244   0.01358  -0.0636   0.2820   1.0000
   8.500   1.2499   0.02311   0.01428  -0.0625   0.2671   1.0000
   8.750   1.2678   0.02382   0.01503  -0.0613   0.2522   1.0000
   9.000   1.2847   0.02458   0.01582  -0.0600   0.2376   1.0000
   9.250   1.3004   0.02539   0.01668  -0.0586   0.2230   1.0000
   9.500   1.3148   0.02625   0.01758  -0.0571   0.2088   1.0000
   9.750   1.3277   0.02717   0.01855  -0.0555   0.1948   1.0000
  10.000   1.3381   0.02816   0.01957  -0.0536   0.1817   1.0000
  10.250   1.3460   0.02924   0.02068  -0.0514   0.1692   1.0000
  10.500   1.3536   0.03041   0.02193  -0.0494   0.1569   1.0000
  10.750   1.3600   0.03172   0.02331  -0.0475   0.1452   1.0000
  11.000   1.3653   0.03319   0.02484  -0.0457   0.1344   1.0000
  11.250   1.3688   0.03487   0.02655  -0.0441   0.1244   1.0000
  11.500   1.3705   0.03677   0.02847  -0.0426   0.1153   1.0000
  11.750   1.3739   0.03869   0.03050  -0.0413   0.1065   1.0000
  12.000   1.3743   0.04093   0.03280  -0.0402   0.0992   1.0000
  12.250   1.3744   0.04331   0.03527  -0.0393   0.0923   1.0000
  12.500   1.3737   0.04591   0.03794  -0.0386   0.0865   1.0000
  12.750   1.3726   0.04865   0.04079  -0.0381   0.0811   1.0000
  13.000   1.3688   0.05178   0.04396  -0.0378   0.0770   1.0000
  13.250   1.3681   0.05472   0.04707  -0.0377   0.0723   1.0000
  13.500   1.3639   0.05815   0.05059  -0.0379   0.0688   1.0000
  13.750   1.3589   0.06176   0.05425  -0.0382   0.0659   1.0000
  14.000   1.3567   0.06522   0.05790  -0.0386   0.0624   1.0000
  14.250   1.3524   0.06905   0.06186  -0.0393   0.0595   1.0000
  14.500   1.3462   0.07322   0.06612  -0.0404   0.0572   1.0000
  14.750   1.3422   0.07722   0.07022  -0.0413   0.0549   1.0000
  15.000   1.3384   0.08139   0.07459  -0.0424   0.0525   1.0000
  15.250   1.3335   0.08581   0.07915  -0.0438   0.0504   1.0000
  15.500   1.3280   0.09038   0.08382  -0.0455   0.0486   1.0000
  15.750   1.3236   0.09472   0.08818  -0.0469   0.0469   1.0000
  16.000   1.3183   0.09960   0.09328  -0.0488   0.0453   1.0000
  16.250   1.3121   0.10475   0.09863  -0.0509   0.0437   1.0000
  16.500   1.3055   0.11002   0.10408  -0.0532   0.0423   1.0000
  16.750   1.2990   0.11536   0.10954  -0.0558   0.0409   1.0000
  17.000   1.2943   0.12037   0.11464  -0.0582   0.0397   1.0000
  17.250   1.2936   0.12434   0.11862  -0.0599   0.0383   1.0000
  17.500   1.2824   0.13117   0.12567  -0.0637   0.0376   1.0000
  17.750   1.2693   0.13861   0.13334  -0.0680   0.0369   1.0000
  18.000   1.2542   0.14682   0.14177  -0.0730   0.0364   1.0000
  18.250   1.2348   0.15651   0.15167  -0.0791   0.0360   1.0000
  18.500   1.2043   0.16993   0.16529  -0.0879   0.0360   1.0000
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