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S1091 (s1091-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 100,000
Max Cl/Cd: 69.9 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1091-il-100000-n5.txt
Download as CSV file: xf-s1091-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.2870   0.09924   0.09457  -0.0171   1.0000   0.0287
  -6.500  -0.2896   0.09781   0.09323  -0.0163   1.0000   0.0295
  -6.250  -0.2886   0.09638   0.09189  -0.0166   1.0000   0.0302
  -6.000  -0.2864   0.09515   0.09074  -0.0179   1.0000   0.0306
  -5.750  -0.2817   0.09400   0.08966  -0.0203   1.0000   0.0309
  -5.500  -0.2716   0.09243   0.08813  -0.0238   0.9997   0.0311
  -5.000  -0.2286   0.08216   0.07790  -0.0298   0.9903   0.0325
  -4.750  -0.2053   0.07806   0.07380  -0.0326   0.9854   0.0341
  -4.500  -0.1765   0.07438   0.07011  -0.0379   0.9786   0.0361
  -4.250  -0.1399   0.07053   0.06622  -0.0453   0.9728   0.0388
  -4.000  -0.0810   0.06746   0.06299  -0.0600   0.9640   0.0426
  -3.750  -0.0259   0.06321   0.05862  -0.0718   0.9591   0.0434
  -3.500  -0.0173   0.05883   0.05432  -0.0700   0.9504   0.0447
  -3.250   0.0134   0.05528   0.05075  -0.0734   0.9451   0.0468
  -3.000   0.0487   0.05205   0.04747  -0.0783   0.9366   0.0495
  -2.750   0.1313   0.04845   0.04346  -0.0947   0.9329   0.0560
  -2.500   0.1616   0.04421   0.03919  -0.0979   0.9242   0.0567
  -2.250   0.2025   0.03886   0.03368  -0.1018   0.9201   0.0296
  -2.000   0.2446   0.03533   0.02997  -0.1066   0.9123   0.0289
  -1.750   0.2954   0.03135   0.02567  -0.1126   0.9078   0.0291
  -1.500   0.3415   0.02759   0.02153  -0.1171   0.9017   0.0282
  -1.000   0.4329   0.02122   0.01397  -0.1239   0.8910   0.0270
  -0.750   0.4700   0.01940   0.01160  -0.1252   0.8818   0.0289
  -0.500   0.5081   0.01793   0.00974  -0.1266   0.8734   0.0329
  -0.250   0.5462   0.01674   0.00835  -0.1280   0.8644   0.0361
   0.000   0.5809   0.01602   0.00744  -0.1288   0.8526   0.0429
   0.250   0.6158   0.01532   0.00665  -0.1297   0.8407   0.0530
   0.500   0.6526   0.01465   0.00604  -0.1308   0.8287   0.1100
   0.750   0.6863   0.01413   0.00600  -0.1319   0.8158   0.2874
   1.000   0.7181   0.01380   0.00585  -0.1323   0.8021   0.4187
   1.250   0.7507   0.01281   0.00556  -0.1328   0.7881   1.0000
   1.500   0.7810   0.01291   0.00543  -0.1328   0.7732   1.0000
   1.750   0.8101   0.01304   0.00536  -0.1326   0.7578   1.0000
   2.000   0.8384   0.01319   0.00534  -0.1323   0.7421   1.0000
   2.250   0.8659   0.01335   0.00536  -0.1318   0.7256   1.0000
   2.500   0.8929   0.01353   0.00540  -0.1312   0.7084   1.0000
   2.750   0.9193   0.01372   0.00547  -0.1305   0.6902   1.0000
   3.000   0.9443   0.01393   0.00561  -0.1296   0.6697   1.0000
   3.250   0.9695   0.01414   0.00571  -0.1286   0.6486   1.0000
   3.500   0.9933   0.01438   0.00586  -0.1275   0.6248   1.0000
   3.750   1.0170   0.01463   0.00601  -0.1263   0.5990   1.0000
   4.000   1.0400   0.01490   0.00618  -0.1250   0.5703   1.0000
   4.250   1.0625   0.01520   0.00642  -0.1236   0.5376   1.0000
   4.500   1.0842   0.01556   0.00663  -0.1222   0.4999   1.0000
   4.750   1.1051   0.01602   0.00687  -0.1206   0.4609   1.0000
   5.000   1.1255   0.01656   0.00720  -0.1191   0.4220   1.0000
   5.250   1.1456   0.01716   0.00761  -0.1175   0.3849   1.0000
   5.500   1.1653   0.01781   0.00814  -0.1160   0.3486   1.0000
   5.750   1.1849   0.01848   0.00866  -0.1145   0.3132   1.0000
   6.000   1.2042   0.01919   0.00923  -0.1131   0.2793   1.0000
   6.250   1.2232   0.01995   0.00984  -0.1116   0.2475   1.0000
   6.500   1.2422   0.02072   0.01051  -0.1102   0.2177   1.0000
   6.750   1.2604   0.02158   0.01128  -0.1087   0.1905   1.0000
   7.000   1.2787   0.02245   0.01207  -0.1072   0.1673   1.0000
   7.250   1.2962   0.02338   0.01292  -0.1057   0.1496   1.0000
   7.750   1.3316   0.02521   0.01480  -0.1025   0.1260   1.0000
   8.000   1.3485   0.02620   0.01588  -0.1008   0.1179   1.0000
   8.250   1.3644   0.02725   0.01696  -0.0991   0.1112   1.0000
   8.500   1.3809   0.02828   0.01809  -0.0974   0.1053   1.0000
   8.750   1.3969   0.02933   0.01922  -0.0957   0.0998   1.0000
   9.000   1.4114   0.03053   0.02045  -0.0938   0.0954   1.0000
   9.250   1.4281   0.03162   0.02177  -0.0922   0.0914   1.0000
   9.500   1.4438   0.03282   0.02310  -0.0905   0.0882   1.0000
   9.750   1.4590   0.03411   0.02448  -0.0889   0.0856   1.0000
  10.000   1.4752   0.03564   0.02606  -0.0875   0.0833   1.0000
  10.250   1.4925   0.03705   0.02774  -0.0861   0.0811   1.0000
  10.500   1.5083   0.03850   0.02945  -0.0845   0.0786   1.0000
  10.750   1.5217   0.03992   0.03110  -0.0828   0.0759   1.0000
  11.000   1.5343   0.04137   0.03268  -0.0810   0.0735   1.0000
  11.250   1.5507   0.04327   0.03465  -0.0800   0.0715   1.0000
  11.500   1.5625   0.04523   0.03695  -0.0781   0.0699   1.0000
  11.750   1.5690   0.04717   0.03928  -0.0757   0.0680   1.0000
  12.000   1.5725   0.04912   0.04156  -0.0731   0.0659   1.0000
  12.250   1.5746   0.05098   0.04367  -0.0706   0.0637   1.0000
  12.500   1.5773   0.05278   0.04564  -0.0684   0.0617   1.0000
  12.750   1.5832   0.05480   0.04775  -0.0668   0.0595   1.0000
  13.000   1.5751   0.05753   0.05087  -0.0643   0.0579   1.0000
  13.250   1.5636   0.06060   0.05434  -0.0622   0.0561   1.0000
  13.500   1.5526   0.06380   0.05787  -0.0608   0.0540   1.0000
  13.750   1.5450   0.06622   0.06045  -0.0601   0.0512   1.0000
  14.000   1.5409   0.06804   0.06214  -0.0601   0.0477   1.0000
  14.250   1.5243   0.07290   0.06744  -0.0607   0.0459   1.0000
  14.500   1.5089   0.07796   0.07284  -0.0621   0.0436   1.0000
  14.750   1.4975   0.08241   0.07746  -0.0642   0.0404   1.0000
  15.000   1.4873   0.08693   0.08195  -0.0670   0.0374   1.0000
  15.250   1.4694   0.09402   0.08938  -0.0701   0.0363   1.0000
  15.500   1.4499   0.10179   0.09742  -0.0740   0.0359   1.0000
  15.750   1.4300   0.11006   0.10589  -0.0783   0.0363   1.0000
  16.000   1.4096   0.11884   0.11484  -0.0831   0.0368   1.0000
  16.250   1.3905   0.12769   0.12382  -0.0882   0.0374   1.0000
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