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S2091-101-83 (s2091-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S2091-101-83 (s2091-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.23 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2091-il-1000000.txt
Download as CSV file: xf-s2091-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2633   0.09406   0.09259  -0.0292   0.9753   0.0134
  -9.750  -0.2531   0.08976   0.08827  -0.0322   0.9593   0.0138
  -9.500  -0.5949   0.02709   0.02447  -0.0822   0.9308   0.0091
  -9.250  -0.5832   0.02383   0.02079  -0.0824   0.9171   0.0093
  -9.000  -0.5659   0.02151   0.01812  -0.0824   0.9066   0.0094
  -8.750  -0.5449   0.02002   0.01635  -0.0821   0.8975   0.0095
  -8.500  -0.5216   0.01879   0.01490  -0.0819   0.8886   0.0097
  -8.250  -0.5025   0.01618   0.01188  -0.0818   0.8801   0.0101
  -8.000  -0.4771   0.01545   0.01105  -0.0816   0.8719   0.0104
  -7.750  -0.4509   0.01502   0.01053  -0.0814   0.8645   0.0108
  -7.500  -0.4244   0.01450   0.00992  -0.0813   0.8566   0.0113
  -7.250  -0.3979   0.01397   0.00926  -0.0811   0.8493   0.0118
  -7.000  -0.3711   0.01340   0.00856  -0.0809   0.8415   0.0122
  -6.750  -0.3440   0.01299   0.00801  -0.0807   0.8343   0.0125
  -6.500  -0.3183   0.01185   0.00673  -0.0806   0.8265   0.0133
  -6.250  -0.2910   0.01151   0.00632  -0.0805   0.8193   0.0139
  -6.000  -0.2633   0.01114   0.00589  -0.0804   0.8116   0.0146
  -5.750  -0.2356   0.01085   0.00549  -0.0802   0.8043   0.0154
  -5.500  -0.2081   0.01027   0.00483  -0.0801   0.7966   0.0164
  -5.000  -0.1523   0.00974   0.00420  -0.0800   0.7815   0.0188
  -4.500  -0.0963   0.00910   0.00344  -0.0799   0.7664   0.0217
  -4.250  -0.0682   0.00891   0.00319  -0.0798   0.7588   0.0233
  -4.000  -0.0398   0.00867   0.00290  -0.0797   0.7509   0.0248
  -3.500   0.0168   0.00827   0.00243  -0.0797   0.7350   0.0296
  -3.250   0.0450   0.00804   0.00216  -0.0796   0.7270   0.0334
  -3.000   0.0736   0.00787   0.00198  -0.0796   0.7185   0.0381
  -2.750   0.1019   0.00773   0.00182  -0.0796   0.7103   0.0460
  -2.500   0.1304   0.00758   0.00169  -0.0796   0.7015   0.0568
  -2.250   0.1588   0.00749   0.00159  -0.0796   0.6930   0.0662
  -2.000   0.1873   0.00737   0.00148  -0.0796   0.6839   0.0775
  -1.750   0.2158   0.00727   0.00139  -0.0796   0.6751   0.0908
  -1.500   0.2441   0.00718   0.00131  -0.0796   0.6658   0.1094
  -1.250   0.2726   0.00705   0.00124  -0.0796   0.6563   0.1377
  -1.000   0.3009   0.00689   0.00119  -0.0797   0.6468   0.1809
  -0.750   0.3289   0.00668   0.00115  -0.0797   0.6366   0.2544
  -0.500   0.3570   0.00646   0.00114  -0.0798   0.6266   0.3332
  -0.250   0.3849   0.00627   0.00114  -0.0799   0.6165   0.4186
   0.000   0.4128   0.00611   0.00115  -0.0799   0.6059   0.5013
   0.250   0.4406   0.00595   0.00117  -0.0799   0.5953   0.5815
   0.500   0.4678   0.00575   0.00121  -0.0797   0.5848   0.6798
   0.750   0.4933   0.00552   0.00127  -0.0791   0.5739   0.7954
   1.000   0.5183   0.00519   0.00129  -0.0779   0.5628   0.9619
   1.250   0.5524   0.00526   0.00129  -0.0792   0.5508   1.0000
   1.500   0.5805   0.00537   0.00132  -0.0792   0.5390   1.0000
   1.750   0.6085   0.00548   0.00136  -0.0791   0.5269   1.0000
   2.000   0.6365   0.00560   0.00141  -0.0791   0.5141   1.0000
   2.250   0.6646   0.00571   0.00146  -0.0791   0.5015   1.0000
   2.500   0.6925   0.00583   0.00152  -0.0790   0.4887   1.0000
   2.750   0.7204   0.00597   0.00159  -0.0790   0.4761   1.0000
   3.000   0.7481   0.00611   0.00167  -0.0789   0.4628   1.0000
   3.250   0.7758   0.00626   0.00176  -0.0789   0.4496   1.0000
   3.500   0.8034   0.00643   0.00186  -0.0788   0.4357   1.0000
   4.000   0.8583   0.00676   0.00208  -0.0787   0.4079   1.0000
   4.250   0.8856   0.00694   0.00220  -0.0786   0.3937   1.0000
   4.500   0.9128   0.00713   0.00233  -0.0785   0.3792   1.0000
   4.750   0.9399   0.00733   0.00248  -0.0784   0.3648   1.0000
   5.000   0.9668   0.00754   0.00263  -0.0783   0.3498   1.0000
   5.250   0.9936   0.00777   0.00279  -0.0781   0.3347   1.0000
   5.500   1.0202   0.00800   0.00298  -0.0780   0.3199   1.0000
   5.750   1.0466   0.00825   0.00316  -0.0778   0.3050   1.0000
   6.000   1.0729   0.00850   0.00336  -0.0776   0.2903   1.0000
   6.250   1.0990   0.00877   0.00358  -0.0774   0.2755   1.0000
   6.500   1.1248   0.00907   0.00380  -0.0772   0.2598   1.0000
   6.750   1.1505   0.00936   0.00404  -0.0769   0.2454   1.0000
   7.000   1.1761   0.00966   0.00429  -0.0767   0.2317   1.0000
   7.250   1.2015   0.00996   0.00455  -0.0764   0.2186   1.0000
   7.500   1.2266   0.01029   0.00483  -0.0761   0.2052   1.0000
   7.750   1.2514   0.01063   0.00512  -0.0757   0.1920   1.0000
   8.000   1.2758   0.01100   0.00544  -0.0753   0.1782   1.0000
   8.250   1.2998   0.01138   0.00577  -0.0748   0.1646   1.0000
   8.500   1.3234   0.01181   0.00613  -0.0743   0.1505   1.0000
   8.750   1.3464   0.01226   0.00652  -0.0738   0.1364   1.0000
   9.000   1.3686   0.01276   0.00695  -0.0731   0.1214   1.0000
   9.250   1.3902   0.01329   0.00741  -0.0724   0.1074   1.0000
   9.500   1.4111   0.01386   0.00791  -0.0715   0.0937   1.0000
   9.750   1.4316   0.01443   0.00843  -0.0706   0.0820   1.0000
  10.000   1.4516   0.01501   0.00896  -0.0696   0.0718   1.0000
  10.250   1.4710   0.01559   0.00952  -0.0686   0.0629   1.0000
  10.500   1.4893   0.01622   0.01011  -0.0674   0.0550   1.0000
  10.750   1.5062   0.01690   0.01075  -0.0660   0.0481   1.0000
  11.000   1.5239   0.01746   0.01134  -0.0647   0.0439   1.0000
  11.250   1.5372   0.01819   0.01206  -0.0628   0.0387   1.0000
  11.500   1.5507   0.01874   0.01264  -0.0608   0.0363   1.0000
  11.750   1.5597   0.01951   0.01342  -0.0583   0.0331   1.0000
  12.000   1.5701   0.02027   0.01422  -0.0561   0.0305   1.0000
  12.250   1.5808   0.02107   0.01506  -0.0542   0.0284   1.0000
  12.500   1.5879   0.02215   0.01615  -0.0520   0.0260   1.0000
  12.750   1.5978   0.02311   0.01717  -0.0503   0.0243   1.0000
  13.000   1.6070   0.02416   0.01827  -0.0487   0.0226   1.0000
  13.250   1.6127   0.02554   0.01967  -0.0470   0.0208   1.0000
  13.500   1.6192   0.02693   0.02113  -0.0455   0.0195   1.0000
  13.750   1.6276   0.02822   0.02250  -0.0443   0.0186   1.0000
  14.000   1.6336   0.02978   0.02410  -0.0431   0.0174   1.0000
  14.250   1.6357   0.03176   0.02613  -0.0418   0.0163   1.0000
  14.500   1.6389   0.03373   0.02819  -0.0409   0.0155   1.0000
  14.750   1.6435   0.03566   0.03020  -0.0401   0.0150   1.0000
  15.000   1.6477   0.03768   0.03229  -0.0395   0.0143   1.0000
  15.250   1.6499   0.03997   0.03466  -0.0390   0.0137   1.0000
  15.500   1.6481   0.04282   0.03757  -0.0387   0.0130   1.0000
  15.750   1.6403   0.04646   0.04132  -0.0386   0.0124   1.0000
  16.000   1.6406   0.04932   0.04428  -0.0387   0.0121   1.0000
  16.250   1.6401   0.05240   0.04745  -0.0390   0.0118   1.0000
  16.500   1.6384   0.05573   0.05089  -0.0396   0.0114   1.0000
  16.750   1.6352   0.05939   0.05466  -0.0403   0.0111   1.0000
  17.000   1.6297   0.06353   0.05889  -0.0414   0.0107   1.0000
  17.250   1.6234   0.06787   0.06332  -0.0426   0.0104   1.0000
  17.500   1.6136   0.07293   0.06849  -0.0443   0.0102   1.0000
  17.750   1.6003   0.07870   0.07438  -0.0464   0.0099   1.0000
  18.000   1.5848   0.08504   0.08085  -0.0489   0.0097   1.0000
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