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S2091-101-83 (s2091-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 500,000
Max Cl/Cd: 99.46 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2091-il-500000-n5.txt
Download as CSV file: xf-s2091-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3796   0.11973   0.11735  -0.0174   1.0000   0.0080
 -11.000  -0.3752   0.11588   0.11351  -0.0190   1.0000   0.0080
  -9.500  -0.5931   0.02815   0.02479  -0.0819   0.9149   0.0082
  -9.250  -0.5802   0.02482   0.02099  -0.0824   0.9025   0.0085
  -9.000  -0.5623   0.02254   0.01833  -0.0825   0.8925   0.0087
  -8.750  -0.5418   0.02080   0.01624  -0.0823   0.8833   0.0089
  -8.500  -0.5196   0.01932   0.01452  -0.0822   0.8745   0.0092
  -8.250  -0.4958   0.01840   0.01344  -0.0819   0.8666   0.0095
  -8.000  -0.4706   0.01763   0.01252  -0.0818   0.8583   0.0098
  -7.750  -0.4455   0.01690   0.01164  -0.0816   0.8508   0.0102
  -7.500  -0.4197   0.01614   0.01072  -0.0814   0.8427   0.0106
  -7.250  -0.3940   0.01542   0.00981  -0.0812   0.8354   0.0111
  -7.000  -0.3676   0.01474   0.00896  -0.0810   0.8274   0.0116
  -6.750  -0.3414   0.01413   0.00823  -0.0808   0.8201   0.0122
  -6.500  -0.3142   0.01376   0.00780  -0.0807   0.8122   0.0130
  -6.000  -0.2599   0.01295   0.00674  -0.0804   0.7971   0.0149
  -5.750  -0.2330   0.01246   0.00617  -0.0803   0.7895   0.0158
  -5.500  -0.2054   0.01210   0.00574  -0.0802   0.7818   0.0169
  -5.250  -0.1779   0.01177   0.00530  -0.0800   0.7741   0.0181
  -5.000  -0.1502   0.01140   0.00485  -0.0799   0.7662   0.0193
  -4.750  -0.1226   0.01113   0.00453  -0.0798   0.7585   0.0209
  -4.500  -0.0946   0.01088   0.00420  -0.0798   0.7504   0.0225
  -4.000  -0.0388   0.01034   0.00356  -0.0796   0.7343   0.0263
  -3.750  -0.0109   0.01016   0.00328  -0.0795   0.7264   0.0283
  -3.500   0.0172   0.00990   0.00302  -0.0795   0.7179   0.0314
  -3.250   0.0453   0.00974   0.00279  -0.0794   0.7098   0.0347
  -3.000   0.0735   0.00954   0.00259  -0.0793   0.7010   0.0400
  -2.750   0.1016   0.00939   0.00241  -0.0793   0.6927   0.0472
  -2.500   0.1298   0.00926   0.00226  -0.0792   0.6834   0.0554
  -2.250   0.1581   0.00916   0.00212  -0.0792   0.6745   0.0632
  -1.750   0.2145   0.00894   0.00189  -0.0791   0.6554   0.0843
  -1.500   0.2426   0.00884   0.00180  -0.0791   0.6460   0.0996
  -1.250   0.2707   0.00872   0.00172  -0.0790   0.6360   0.1246
  -1.000   0.2987   0.00858   0.00165  -0.0791   0.6258   0.1606
  -0.750   0.3267   0.00845   0.00160  -0.0791   0.6157   0.2028
  -0.500   0.3546   0.00832   0.00156  -0.0791   0.6050   0.2518
  -0.250   0.3825   0.00816   0.00155  -0.0791   0.5941   0.3164
   0.000   0.4102   0.00802   0.00155  -0.0791   0.5833   0.3848
   0.250   0.4378   0.00791   0.00156  -0.0790   0.5719   0.4507
   0.500   0.4652   0.00776   0.00159  -0.0790   0.5602   0.5316
   0.750   0.4919   0.00755   0.00165  -0.0787   0.5489   0.6331
   1.000   0.5164   0.00727   0.00173  -0.0779   0.5376   0.7622
   1.250   0.5393   0.00694   0.00176  -0.0763   0.5263   0.9342
   1.500   0.5751   0.00702   0.00177  -0.0779   0.5130   1.0000
   1.750   0.6028   0.00714   0.00181  -0.0778   0.5007   1.0000
   2.000   0.6305   0.00728   0.00187  -0.0777   0.4880   1.0000
   2.250   0.6580   0.00743   0.00194  -0.0776   0.4754   1.0000
   2.500   0.6855   0.00758   0.00201  -0.0775   0.4624   1.0000
   2.750   0.7129   0.00775   0.00210  -0.0774   0.4493   1.0000
   3.250   0.7674   0.00809   0.00232  -0.0772   0.4225   1.0000
   3.500   0.7946   0.00827   0.00244  -0.0770   0.4093   1.0000
   3.750   0.8217   0.00847   0.00258  -0.0769   0.3958   1.0000
   4.000   0.8486   0.00867   0.00272  -0.0768   0.3824   1.0000
   4.250   0.8754   0.00889   0.00287  -0.0766   0.3690   1.0000
   4.500   0.9020   0.00911   0.00305  -0.0764   0.3553   1.0000
   4.750   0.9285   0.00935   0.00323  -0.0762   0.3418   1.0000
   5.000   0.9548   0.00960   0.00343  -0.0760   0.3276   1.0000
   5.250   0.9809   0.00987   0.00364  -0.0758   0.3139   1.0000
   5.500   1.0069   0.01014   0.00386  -0.0756   0.3002   1.0000
   5.750   1.0327   0.01043   0.00410  -0.0753   0.2858   1.0000
   6.000   1.0583   0.01072   0.00435  -0.0750   0.2720   1.0000
   6.250   1.0838   0.01102   0.00462  -0.0747   0.2585   1.0000
   6.500   1.1089   0.01135   0.00490  -0.0744   0.2447   1.0000
   6.750   1.1338   0.01169   0.00520  -0.0741   0.2310   1.0000
   7.000   1.1584   0.01205   0.00552  -0.0737   0.2170   1.0000
   7.250   1.1825   0.01245   0.00586  -0.0732   0.2023   1.0000
   7.500   1.2064   0.01285   0.00622  -0.0728   0.1885   1.0000
   7.750   1.2300   0.01326   0.00659  -0.0723   0.1757   1.0000
   8.000   1.2533   0.01368   0.00699  -0.0717   0.1636   1.0000
   8.250   1.2760   0.01415   0.00741  -0.0711   0.1507   1.0000
   8.500   1.2981   0.01464   0.00786  -0.0704   0.1376   1.0000
   8.750   1.3195   0.01518   0.00836  -0.0697   0.1241   1.0000
   9.000   1.3402   0.01574   0.00888  -0.0688   0.1113   1.0000
   9.250   1.3601   0.01634   0.00944  -0.0679   0.0991   1.0000
   9.500   1.3793   0.01697   0.01003  -0.0668   0.0880   1.0000
   9.750   1.3973   0.01764   0.01067  -0.0656   0.0774   1.0000
  10.000   1.4147   0.01831   0.01131  -0.0644   0.0684   1.0000
  10.250   1.4312   0.01898   0.01199  -0.0630   0.0607   1.0000
  10.500   1.4454   0.01970   0.01270  -0.0612   0.0543   1.0000
  10.750   1.4571   0.02042   0.01344  -0.0591   0.0490   1.0000
  11.000   1.4684   0.02118   0.01424  -0.0570   0.0450   1.0000
  11.250   1.4793   0.02200   0.01509  -0.0551   0.0414   1.0000
  11.500   1.4886   0.02298   0.01609  -0.0531   0.0381   1.0000
  11.750   1.4995   0.02389   0.01707  -0.0515   0.0355   1.0000
  12.000   1.5081   0.02502   0.01824  -0.0498   0.0327   1.0000
  12.250   1.5163   0.02623   0.01950  -0.0482   0.0304   1.0000
  12.500   1.5254   0.02744   0.02079  -0.0468   0.0286   1.0000
  12.750   1.5324   0.02886   0.02227  -0.0455   0.0267   1.0000
  13.000   1.5377   0.03050   0.02397  -0.0442   0.0251   1.0000
  13.250   1.5449   0.03204   0.02560  -0.0432   0.0239   1.0000
  13.500   1.5508   0.03376   0.02740  -0.0422   0.0226   1.0000
  13.750   1.5547   0.03574   0.02945  -0.0414   0.0213   1.0000
  14.000   1.5564   0.03801   0.03180  -0.0406   0.0201   1.0000
  14.250   1.5597   0.04022   0.03410  -0.0401   0.0192   1.0000
  14.500   1.5622   0.04260   0.03659  -0.0398   0.0184   1.0000
  14.750   1.5631   0.04523   0.03932  -0.0396   0.0176   1.0000
  15.000   1.5621   0.04817   0.04235  -0.0396   0.0168   1.0000
  15.250   1.5590   0.05149   0.04575  -0.0398   0.0161   1.0000
  15.500   1.5566   0.05486   0.04923  -0.0402   0.0155   1.0000
  15.750   1.5547   0.05830   0.05279  -0.0408   0.0149   1.0000
  16.000   1.5516   0.06201   0.05662  -0.0416   0.0143   1.0000
  16.250   1.5471   0.06607   0.06079  -0.0427   0.0138   1.0000
  16.500   1.5409   0.07049   0.06532  -0.0440   0.0134   1.0000
  16.750   1.5333   0.07528   0.07022  -0.0456   0.0130   1.0000
  17.000   1.5236   0.08055   0.07560  -0.0476   0.0126   1.0000
  17.250   1.5131   0.08610   0.08128  -0.0497   0.0123   1.0000
  17.500   1.5057   0.09130   0.08661  -0.0519   0.0120   1.0000
  17.750   1.4965   0.09686   0.09231  -0.0542   0.0117   1.0000
  18.000   1.4870   0.10258   0.09816  -0.0568   0.0114   1.0000
  18.250   1.4768   0.10856   0.10427  -0.0595   0.0112   1.0000
  18.500   1.4667   0.11462   0.11045  -0.0625   0.0109   1.0000
  18.750   1.4556   0.12093   0.11688  -0.0656   0.0107   1.0000
  19.000   1.4447   0.12730   0.12336  -0.0689   0.0105   1.0000
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