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S1091 (s1091-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 100,000
Max Cl/Cd: 70.57 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1091-il-100000.txt
Download as CSV file: xf-s1091-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1091                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.2904   0.09946   0.09487  -0.0170   1.0000   0.0424
  -6.500  -0.2919   0.09764   0.09312  -0.0157   1.0000   0.0434
  -6.250  -0.2910   0.09570   0.09126  -0.0151   1.0000   0.0443
  -6.000  -0.2901   0.09371   0.08933  -0.0147   1.0000   0.0457
  -5.750  -0.2887   0.09185   0.08754  -0.0147   1.0000   0.0470
  -5.500  -0.2861   0.09020   0.08596  -0.0153   1.0000   0.0482
  -5.250  -0.2800   0.08917   0.08499  -0.0179   1.0000   0.0495
  -5.000  -0.2640   0.08898   0.08481  -0.0249   1.0000   0.0503
  -4.750  -0.2435   0.08791   0.08373  -0.0314   1.0000   0.0506
  -4.500  -0.2502   0.08304   0.07898  -0.0268   1.0000   0.0513
  -4.250  -0.2553   0.07953   0.07555  -0.0220   1.0000   0.0523
  -4.000  -0.2529   0.07698   0.07305  -0.0203   1.0000   0.0537
  -3.750  -0.2450   0.07467   0.07077  -0.0206   1.0000   0.0555
  -3.500  -0.2321   0.07238   0.06849  -0.0225   1.0000   0.0580
  -3.250  -0.1467   0.07119   0.06700  -0.0448   0.9972   0.0641
  -3.000  -0.1380   0.06513   0.06106  -0.0430   0.9921   0.0657
  -2.750  -0.1071   0.06136   0.05729  -0.0463   0.9861   0.0701
  -2.500  -0.0289   0.05763   0.05331  -0.0630   0.9795   0.0791
  -2.250  -0.0038   0.05384   0.04957  -0.0642   0.9736   0.0838
  -2.000   0.0548   0.05033   0.04589  -0.0744   0.9667   0.0949
  -1.750   0.1056   0.04709   0.04251  -0.0818   0.9609   0.1094
  -1.500   0.1518   0.04412   0.03942  -0.0877   0.9539   0.1240
  -1.250   0.2158   0.04209   0.03704  -0.0969   0.9479   0.1505
  -1.000   0.2511   0.03871   0.03368  -0.0998   0.9408   0.1661
  -0.750   0.2937   0.03597   0.03090  -0.1034   0.9346   0.1855
  -0.500   0.3843   0.02989   0.02347  -0.1146   0.9332   0.0932
  -0.250   0.4281   0.02700   0.02002  -0.1170   0.9254   0.0773
   0.000   0.4783   0.02438   0.01696  -0.1206   0.9205   0.0724
   0.250   0.5182   0.02278   0.01492  -0.1220   0.9116   0.0724
   0.500   0.5674   0.02131   0.01323  -0.1252   0.9060   0.0847
   0.750   0.6043   0.02030   0.01218  -0.1261   0.8959   0.1052
   1.000   0.6573   0.01858   0.01136  -0.1302   0.8917   0.3933
   1.250   0.6965   0.01709   0.01062  -0.1317   0.8816   1.0000
   1.500   0.7392   0.01680   0.01004  -0.1337   0.8723   1.0000
   1.750   0.7848   0.01636   0.00940  -0.1362   0.8637   1.0000
   2.000   0.8209   0.01616   0.00907  -0.1370   0.8510   1.0000
   2.250   0.8572   0.01593   0.00874  -0.1377   0.8377   1.0000
   2.500   0.8928   0.01571   0.00844  -0.1382   0.8231   1.0000
   3.000   0.9576   0.01545   0.00805  -0.1379   0.7887   1.0000
   3.250   0.9850   0.01547   0.00800  -0.1369   0.7677   1.0000
   3.500   1.0142   0.01545   0.00788  -0.1361   0.7468   1.0000
   3.750   1.0385   0.01555   0.00793  -0.1345   0.7225   1.0000
   4.000   1.0630   0.01566   0.00802  -0.1330   0.6972   1.0000
   4.250   1.0870   0.01578   0.00805  -0.1313   0.6704   1.0000
   4.500   1.1098   0.01594   0.00813  -0.1296   0.6413   1.0000
   4.750   1.1316   0.01612   0.00823  -0.1277   0.6097   1.0000
   5.000   1.1528   0.01634   0.00835  -0.1257   0.5758   1.0000
   5.250   1.1728   0.01662   0.00859  -0.1236   0.5372   1.0000
   5.500   1.1920   0.01699   0.00881  -0.1215   0.4956   1.0000
   5.750   1.2101   0.01753   0.00912  -0.1193   0.4511   1.0000
   6.000   1.2274   0.01825   0.00960  -0.1171   0.4056   1.0000
   6.250   1.2435   0.01913   0.01020  -0.1148   0.3595   1.0000
   6.500   1.2588   0.02015   0.01100  -0.1125   0.3133   1.0000
   6.750   1.2735   0.02133   0.01190  -0.1103   0.2692   1.0000
   7.000   1.2885   0.02260   0.01292  -0.1081   0.2321   1.0000
   7.250   1.3046   0.02391   0.01401  -0.1062   0.2042   1.0000
   7.500   1.3223   0.02525   0.01520  -0.1046   0.1838   1.0000
   7.750   1.3420   0.02662   0.01655  -0.1032   0.1690   1.0000
   8.000   1.3637   0.02812   0.01794  -0.1023   0.1580   1.0000
   8.250   1.3862   0.02949   0.01939  -0.1014   0.1490   1.0000
   8.500   1.4100   0.03114   0.02111  -0.1007   0.1418   1.0000
   8.750   1.4326   0.03256   0.02261  -0.1000   0.1349   1.0000
   9.000   1.4561   0.03439   0.02457  -0.0994   0.1293   1.0000
   9.250   1.4781   0.03614   0.02660  -0.0984   0.1250   1.0000
   9.500   1.5012   0.03804   0.02862  -0.0978   0.1213   1.0000
   9.750   1.5255   0.04083   0.03153  -0.0976   0.1182   1.0000
  10.000   1.5392   0.04296   0.03424  -0.0954   0.1157   1.0000
  10.250   1.5529   0.04512   0.03681  -0.0935   0.1121   1.0000
  10.500   1.5696   0.04733   0.03924  -0.0922   0.1088   1.0000
  10.750   1.5866   0.05041   0.04250  -0.0912   0.1064   1.0000
  11.000   1.5914   0.05407   0.04662  -0.0887   0.1045   1.0000
  11.250   1.5868   0.05717   0.05033  -0.0849   0.1025   1.0000
  11.500   1.5803   0.06050   0.05414  -0.0813   0.1003   1.0000
  11.750   1.5726   0.06397   0.05799  -0.0779   0.0985   1.0000
  12.000   1.5661   0.06728   0.06158  -0.0749   0.0967   1.0000
  12.250   1.5866   0.07055   0.06478  -0.0752   0.0919   1.0000
  12.500   1.5611   0.07409   0.06868  -0.0706   0.0916   1.0000
  12.750   1.5336   0.07801   0.07288  -0.0667   0.0914   1.0000
  13.000   1.5053   0.08269   0.07776  -0.0642   0.0915   1.0000
  13.250   1.4766   0.08820   0.08349  -0.0633   0.0917   1.0000
  13.500   1.4482   0.09459   0.09006  -0.0639   0.0920   1.0000
  13.750   1.4208   0.10190   0.09752  -0.0657   0.0923   1.0000
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