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S1091 (s1091-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 500,000
Max Cl/Cd: 129.79 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1091-il-500000.txt
Download as CSV file: xf-s1091-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3009   0.09918   0.09705  -0.0140   1.0000   0.0076
  -7.000  -0.3034   0.09752   0.09542  -0.0124   1.0000   0.0077
  -6.750  -0.3095   0.09612   0.09407  -0.0102   1.0000   0.0078
  -6.500  -0.2991   0.09338   0.09135  -0.0124   0.9981   0.0080
  -6.250  -0.2718   0.08930   0.08725  -0.0189   0.9950   0.0083
  -6.000  -0.2444   0.08500   0.08296  -0.0254   0.9909   0.0089
  -5.750  -0.2057   0.08064   0.07858  -0.0361   0.9868   0.0096
  -5.500  -0.1645   0.07614   0.07405  -0.0474   0.9841   0.0097
  -5.250  -0.1329   0.07203   0.06992  -0.0544   0.9783   0.0098
  -5.000  -0.1183   0.06779   0.06571  -0.0547   0.9756   0.0103
  -4.750  -0.0835   0.06411   0.06201  -0.0614   0.9733   0.0110
  -4.500  -0.0516   0.06058   0.05846  -0.0673   0.9679   0.0119
  -4.250  -0.0129   0.05664   0.05448  -0.0747   0.9634   0.0126
  -4.000   0.0396   0.05233   0.05010  -0.0853   0.9608   0.0134
  -3.750   0.0946   0.04799   0.04568  -0.0957   0.9592   0.0137
  -3.500   0.1307   0.04441   0.04204  -0.1007   0.9506   0.0138
  -3.250   0.1720   0.03928   0.03685  -0.1079   0.9475   0.0143
  -3.000   0.2026   0.03667   0.03421  -0.1108   0.9394   0.0150
  -2.750   0.2459   0.03337   0.03082  -0.1164   0.9343   0.0160
  -2.500   0.2906   0.02976   0.02708  -0.1219   0.9251   0.0176
  -2.250   0.3533   0.02517   0.02218  -0.1298   0.9198   0.0195
  -0.750   0.5826   0.00960   0.00411  -0.1434   0.8229   0.0211
  -0.500   0.6099   0.00903   0.00330  -0.1427   0.8051   0.0205
  -0.250   0.6363   0.00850   0.00264  -0.1421   0.7882   0.0218
   0.000   0.6624   0.00829   0.00235  -0.1414   0.7724   0.0252
   0.250   0.6886   0.00812   0.00205  -0.1407   0.7574   0.0284
   0.500   0.7148   0.00798   0.00181  -0.1400   0.7429   0.0369
   0.750   0.7403   0.00771   0.00182  -0.1394   0.7285   0.1619
   1.000   0.7657   0.00764   0.00187  -0.1387   0.7141   0.2436
   1.250   0.7907   0.00755   0.00198  -0.1381   0.6997   0.3637
   1.500   0.8150   0.00736   0.00211  -0.1373   0.6849   0.5346
   1.750   0.8447   0.00666   0.00211  -0.1376   0.6691   1.0000
   2.000   0.8700   0.00680   0.00213  -0.1368   0.6528   1.0000
   2.250   0.8952   0.00695   0.00217  -0.1360   0.6357   1.0000
   2.500   0.9200   0.00713   0.00222  -0.1352   0.6169   1.0000
   2.750   0.9449   0.00728   0.00230  -0.1344   0.5958   1.0000
   3.000   0.9693   0.00748   0.00237  -0.1335   0.5732   1.0000
   3.250   0.9932   0.00770   0.00246  -0.1326   0.5420   1.0000
   3.500   1.0161   0.00801   0.00257  -0.1314   0.5026   1.0000
   3.750   1.0389   0.00836   0.00273  -0.1303   0.4633   1.0000
   4.000   1.0617   0.00875   0.00295  -0.1293   0.4275   1.0000
   4.250   1.0844   0.00917   0.00318  -0.1283   0.3906   1.0000
   4.500   1.1072   0.00959   0.00342  -0.1273   0.3572   1.0000
   4.750   1.1302   0.00999   0.00368  -0.1264   0.3260   1.0000
   5.000   1.1533   0.01040   0.00394  -0.1255   0.2972   1.0000
   5.250   1.1762   0.01082   0.00425  -0.1246   0.2678   1.0000
   5.500   1.1988   0.01127   0.00456  -0.1236   0.2378   1.0000
   5.750   1.2210   0.01177   0.00491  -0.1226   0.2074   1.0000
   6.000   1.2429   0.01230   0.00529  -0.1216   0.1787   1.0000
   6.250   1.2646   0.01284   0.00571  -0.1205   0.1534   1.0000
   6.500   1.2859   0.01341   0.00616  -0.1194   0.1314   1.0000
   6.750   1.3076   0.01394   0.00661  -0.1183   0.1139   1.0000
   7.000   1.3290   0.01448   0.00709  -0.1172   0.1007   1.0000
   7.250   1.3500   0.01506   0.00764  -0.1161   0.0911   1.0000
   7.500   1.3717   0.01554   0.00813  -0.1150   0.0846   1.0000
   7.750   1.3915   0.01620   0.00879  -0.1136   0.0789   1.0000
   8.000   1.4133   0.01664   0.00930  -0.1125   0.0757   1.0000
   8.250   1.4341   0.01716   0.00987  -0.1113   0.0725   1.0000
   8.500   1.4523   0.01791   0.01064  -0.1097   0.0691   1.0000
   8.750   1.4696   0.01873   0.01154  -0.1079   0.0668   1.0000
   9.000   1.4898   0.01924   0.01215  -0.1066   0.0654   1.0000
   9.250   1.5094   0.01979   0.01278  -0.1053   0.0636   1.0000
   9.500   1.5280   0.02039   0.01348  -0.1038   0.0619   1.0000
   9.750   1.5464   0.02096   0.01411  -0.1023   0.0596   1.0000
  10.000   1.5604   0.02193   0.01511  -0.1002   0.0568   1.0000
  10.250   1.5785   0.02243   0.01570  -0.0988   0.0542   1.0000
  10.500   1.5990   0.02261   0.01596  -0.0977   0.0516   1.0000
  10.750   1.6167   0.02298   0.01639  -0.0961   0.0489   1.0000
  11.000   1.6284   0.02377   0.01721  -0.0937   0.0456   1.0000
  11.250   1.6490   0.02391   0.01743  -0.0927   0.0424   1.0000
  11.500   1.6694   0.02407   0.01760  -0.0918   0.0379   1.0000
  11.750   1.6841   0.02466   0.01822  -0.0899   0.0336   1.0000
  12.000   1.6955   0.02555   0.01893  -0.0879   0.0182   1.0000
  12.250   1.6846   0.02820   0.02150  -0.0828   0.0056   1.0000
  12.500   1.6837   0.03014   0.02357  -0.0793   0.0038   1.0000
  12.750   1.6855   0.03189   0.02549  -0.0764   0.0031   1.0000
  13.000   1.6843   0.03398   0.02774  -0.0735   0.0026   1.0000
  13.250   1.6803   0.03643   0.03040  -0.0708   0.0024   1.0000
  13.500   1.6796   0.03866   0.03281  -0.0687   0.0022   1.0000
  13.750   1.6760   0.04132   0.03566  -0.0669   0.0021   1.0000
  14.000   1.6707   0.04432   0.03885  -0.0654   0.0020   1.0000
  14.250   1.6638   0.04772   0.04243  -0.0645   0.0019   1.0000
  14.500   1.6559   0.05148   0.04635  -0.0640   0.0019   1.0000
  14.750   1.6454   0.05583   0.05088  -0.0640   0.0019   1.0000
  15.000   1.6335   0.06067   0.05590  -0.0647   0.0018   1.0000
  15.250   1.6193   0.06621   0.06162  -0.0660   0.0018   1.0000
  15.500   1.6044   0.07219   0.06779  -0.0679   0.0018   1.0000
  15.750   1.5872   0.07901   0.07480  -0.0706   0.0018   1.0000
  16.000   1.5687   0.08657   0.08254  -0.0739   0.0018   1.0000
  16.250   1.5493   0.09476   0.09092  -0.0779   0.0018   1.0000
  16.500   1.5279   0.10382   0.10016  -0.0826   0.0018   1.0000
  16.750   1.5060   0.11330   0.10982  -0.0877   0.0018   1.0000
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