Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S2091-101-83 (s2091-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 100,000
Max Cl/Cd: 54.74 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2091-il-100000.txt
Download as CSV file: xf-s2091-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3108   0.10138   0.09661  -0.0298   1.0000   0.0903
  -8.500  -0.3184   0.09966   0.09500  -0.0335   1.0000   0.0924
  -8.250  -0.3386   0.09889   0.09441  -0.0379   1.0000   0.0932
  -8.000  -0.3065   0.09232   0.08779  -0.0335   1.0000   0.0967
  -7.750  -0.3004   0.08967   0.08520  -0.0329   1.0000   0.0995
  -7.500  -0.3045   0.08764   0.08327  -0.0325   1.0000   0.1026
  -7.250  -0.3230   0.08676   0.08254  -0.0301   1.0000   0.1044
  -7.000  -0.3496   0.08663   0.08256  -0.0260   1.0000   0.1050
  -6.750  -0.3734   0.08602   0.08206  -0.0241   1.0000   0.1060
  -6.500  -0.4002   0.08503   0.08114  -0.0281   1.0000   0.1074
  -6.250  -0.4134   0.08184   0.07794  -0.0323   1.0000   0.1085
  -6.000  -0.3981   0.07848   0.07469  -0.0260   0.9977   0.1106
  -5.750  -0.3693   0.07467   0.07085  -0.0292   0.9915   0.1168
  -5.500  -0.3349   0.06796   0.06401  -0.0431   0.9827   0.1259
  -5.250  -0.2993   0.06255   0.05834  -0.0547   0.9734   0.1396
  -5.000  -0.2746   0.06010   0.05599  -0.0534   0.9670   0.1490
  -4.750  -0.2405   0.05576   0.05153  -0.0596   0.9597   0.1622
  -4.500  -0.1859   0.04028   0.03447  -0.0769   0.9510   0.0923
  -4.250  -0.1470   0.03530   0.02913  -0.0809   0.9454   0.0875
  -4.000  -0.1114   0.03135   0.02451  -0.0834   0.9379   0.0858
  -3.750  -0.0700   0.02842   0.02094  -0.0862   0.9316   0.0878
  -3.500  -0.0294   0.02655   0.01840  -0.0883   0.9249   0.0928
  -3.250   0.0082   0.02472   0.01645  -0.0903   0.9176   0.1000
  -3.000   0.0565   0.02311   0.01457  -0.0937   0.9135   0.1118
  -2.750   0.0850   0.02229   0.01368  -0.0937   0.9031   0.1260
  -2.500   0.1289   0.02121   0.01262  -0.0962   0.8981   0.1507
  -2.250   0.1548   0.02056   0.01210  -0.0958   0.8872   0.1759
  -2.000   0.1883   0.01980   0.01150  -0.0965   0.8795   0.2178
  -1.750   0.2178   0.01888   0.01106  -0.0966   0.8704   0.2989
  -1.500   0.2394   0.01761   0.01104  -0.0950   0.8611   0.5755
  -1.250   0.2895   0.01636   0.01058  -0.0965   0.8553   1.0000
  -1.000   0.3167   0.01649   0.01043  -0.0962   0.8448   1.0000
  -0.750   0.3483   0.01644   0.01011  -0.0962   0.8368   1.0000
  -0.500   0.3724   0.01663   0.01010  -0.0953   0.8249   1.0000
  -0.250   0.3989   0.01673   0.01002  -0.0946   0.8146   1.0000
   0.000   0.4277   0.01668   0.00979  -0.0940   0.8060   1.0000
   0.250   0.4521   0.01685   0.00983  -0.0931   0.7940   1.0000
   0.500   0.4783   0.01693   0.00978  -0.0923   0.7837   1.0000
   0.750   0.5063   0.01686   0.00956  -0.0915   0.7748   1.0000
   1.000   0.5311   0.01702   0.00963  -0.0906   0.7626   1.0000
   1.250   0.5569   0.01711   0.00963  -0.0898   0.7515   1.0000
   1.500   0.5853   0.01698   0.00937  -0.0889   0.7430   1.0000
   1.750   0.6102   0.01713   0.00946  -0.0881   0.7302   1.0000
   2.000   0.6358   0.01724   0.00951  -0.0872   0.7181   1.0000
   2.250   0.6623   0.01728   0.00947  -0.0864   0.7070   1.0000
   2.500   0.6902   0.01720   0.00929  -0.0856   0.6970   1.0000
   2.750   0.7156   0.01734   0.00939  -0.0848   0.6838   1.0000
   3.000   0.7414   0.01746   0.00947  -0.0840   0.6708   1.0000
   3.250   0.7675   0.01755   0.00954  -0.0833   0.6581   1.0000
   3.500   0.7941   0.01762   0.00955  -0.0825   0.6456   1.0000
   3.750   0.8212   0.01766   0.00951  -0.0818   0.6334   1.0000
   4.000   0.8479   0.01773   0.00953  -0.0810   0.6203   1.0000
   4.250   0.8737   0.01788   0.00967  -0.0803   0.6059   1.0000
   4.500   0.8995   0.01805   0.00981  -0.0796   0.5914   1.0000
   4.750   0.9252   0.01823   0.00997  -0.0789   0.5766   1.0000
   5.000   0.9509   0.01843   0.01016  -0.0782   0.5616   1.0000
   5.250   0.9765   0.01865   0.01036  -0.0775   0.5464   1.0000
   5.500   1.0020   0.01889   0.01057  -0.0768   0.5309   1.0000
   5.750   1.0273   0.01916   0.01083  -0.0760   0.5152   1.0000
   6.000   1.0525   0.01945   0.01109  -0.0753   0.4993   1.0000
   6.250   1.0775   0.01977   0.01137  -0.0746   0.4833   1.0000
   6.500   1.1020   0.02014   0.01173  -0.0739   0.4670   1.0000
   6.750   1.1254   0.02056   0.01219  -0.0730   0.4498   1.0000
   7.000   1.1487   0.02100   0.01266  -0.0722   0.4327   1.0000
   7.250   1.1717   0.02146   0.01313  -0.0714   0.4156   1.0000
   7.500   1.1945   0.02195   0.01364  -0.0705   0.3986   1.0000
   7.750   1.2170   0.02245   0.01414  -0.0696   0.3817   1.0000
   8.000   1.2390   0.02298   0.01466  -0.0686   0.3648   1.0000
   8.250   1.2607   0.02354   0.01522  -0.0677   0.3480   1.0000
   8.500   1.2817   0.02416   0.01579  -0.0666   0.3312   1.0000
   8.750   1.3003   0.02483   0.01655  -0.0654   0.3136   1.0000
   9.000   1.3183   0.02553   0.01731  -0.0640   0.2960   1.0000
   9.250   1.3355   0.02626   0.01809  -0.0626   0.2786   1.0000
   9.500   1.3518   0.02704   0.01888  -0.0611   0.2613   1.0000
   9.750   1.3668   0.02789   0.01971  -0.0596   0.2442   1.0000
  10.000   1.3807   0.02887   0.02064  -0.0579   0.2274   1.0000
  10.250   1.3906   0.02994   0.02180  -0.0558   0.2102   1.0000
  10.500   1.3993   0.03111   0.02303  -0.0536   0.1938   1.0000
  10.750   1.4061   0.03239   0.02432  -0.0512   0.1783   1.0000
  11.000   1.4104   0.03375   0.02568  -0.0486   0.1645   1.0000
  11.250   1.4139   0.03526   0.02719  -0.0461   0.1520   1.0000
  11.500   1.4178   0.03689   0.02878  -0.0438   0.1407   1.0000
  11.750   1.4229   0.03861   0.03043  -0.0419   0.1301   1.0000
  12.000   1.4234   0.04055   0.03258  -0.0397   0.1211   1.0000
  12.250   1.4284   0.04261   0.03466  -0.0381   0.1128   1.0000
  12.500   1.4343   0.04455   0.03657  -0.0367   0.1052   1.0000
  12.750   1.4367   0.04703   0.03925  -0.0352   0.0989   1.0000
  13.000   1.4454   0.04904   0.04117  -0.0342   0.0923   1.0000
  13.250   1.4459   0.05190   0.04430  -0.0330   0.0877   1.0000
  13.500   1.4462   0.05449   0.04705  -0.0319   0.0832   1.0000
  13.750   1.4590   0.05711   0.04960  -0.0313   0.0782   1.0000
  14.000   1.4507   0.06055   0.05340  -0.0304   0.0758   1.0000
  14.250   1.4440   0.06405   0.05718  -0.0298   0.0731   1.0000
  14.500   1.4473   0.06681   0.05998  -0.0295   0.0699   1.0000
  14.750   1.4494   0.07070   0.06394  -0.0292   0.0670   1.0000
  15.000   1.4311   0.07554   0.06913  -0.0296   0.0662   1.0000
  15.250   1.4120   0.08094   0.07486  -0.0307   0.0655   1.0000
  15.500   1.3901   0.08702   0.08123  -0.0326   0.0650   1.0000
  15.750   1.3651   0.09390   0.08840  -0.0354   0.0648   1.0000
  16.000   1.3371   0.10179   0.09656  -0.0392   0.0650   1.0000
  16.250   1.3054   0.11101   0.10603  -0.0444   0.0655   1.0000
  16.500   1.2710   0.12167   0.11689  -0.0509   0.0663   1.0000
  16.750   1.2352   0.13373   0.12910  -0.0586   0.0672   1.0000
<< Back to S2091-101-83 (s2091-il)

Polar data table (+)

Polar graphs


<< Back to S2091-101-83 (s2091-il)