Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S1091 (s1091-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 1,000,000
Max Cl/Cd: 152.99 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1091-il-1000000.txt
Download as CSV file: xf-s1091-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2682   0.12756   0.12598  -0.0192   1.0000   0.0043
 -11.000  -0.2651   0.12491   0.12334  -0.0193   1.0000   0.0043
 -10.750  -0.2621   0.12224   0.12067  -0.0194   1.0000   0.0044
  -8.500  -0.2192   0.09433   0.09284  -0.0245   0.9978   0.0044
  -8.250  -0.2076   0.09039   0.08891  -0.0265   0.9968   0.0045
  -8.000  -0.1954   0.08666   0.08519  -0.0289   0.9958   0.0046
  -7.750  -0.1824   0.08292   0.08145  -0.0316   0.9950   0.0048
  -7.500  -0.1710   0.07933   0.07786  -0.0339   0.9934   0.0048
  -7.250  -0.1589   0.07572   0.07426  -0.0363   0.9913   0.0050
  -7.000  -0.1455   0.07202   0.07055  -0.0391   0.9893   0.0051
  -6.750  -0.1307   0.06818   0.06672  -0.0424   0.9874   0.0054
  -6.500  -0.1148   0.06422   0.06276  -0.0461   0.9857   0.0057
  -6.250  -0.1022   0.06075   0.05930  -0.0488   0.9820   0.0060
  -6.000  -0.1682   0.07761   0.07607  -0.0459   0.9855   0.0054
  -5.750  -0.1418   0.07380   0.07226  -0.0518   0.9829   0.0059
  -5.500  -0.1151   0.07003   0.06848  -0.0574   0.9783   0.0064
  -5.250  -0.0719   0.06523   0.06365  -0.0686   0.9753   0.0067
  -4.500   0.0172   0.05404   0.05242  -0.0847   0.9651   0.0074
  -4.250   0.0555   0.05045   0.04880  -0.0916   0.9621   0.0078
  -4.000   0.0989   0.04658   0.04489  -0.0994   0.9599   0.0083
  -3.750   0.1293   0.04334   0.04162  -0.1035   0.9497   0.0087
  -3.500   0.1740   0.03938   0.03759  -0.1106   0.9411   0.0093
  -3.250   0.2324   0.03483   0.03292  -0.1204   0.9332   0.0096
  -3.000   0.2901   0.03020   0.02814  -0.1297   0.9204   0.0097
  -1.750   0.4744   0.01338   0.00966  -0.1448   0.7999   0.0127
  -1.500   0.5040   0.00988   0.00534  -0.1441   0.7824   0.0094
  -1.250   0.5300   0.00890   0.00406  -0.1435   0.7654   0.0110
  -1.000   0.5559   0.00850   0.00351  -0.1429   0.7496   0.0118
  -0.750   0.5820   0.00837   0.00325  -0.1422   0.7347   0.0133
  -0.500   0.6083   0.00797   0.00271  -0.1416   0.7210   0.0136
  -0.250   0.6346   0.00760   0.00222  -0.1409   0.7076   0.0139
   0.000   0.6607   0.00709   0.00158  -0.1403   0.6945   0.0162
   0.250   0.6869   0.00700   0.00142  -0.1398   0.6811   0.0185
   0.500   0.7132   0.00692   0.00124  -0.1392   0.6681   0.0212
   0.750   0.7394   0.00687   0.00114  -0.1386   0.6547   0.0306
   1.000   0.7651   0.00670   0.00118  -0.1381   0.6407   0.1365
   1.250   0.7909   0.00666   0.00123  -0.1375   0.6256   0.2012
   1.500   0.8166   0.00665   0.00129  -0.1370   0.6096   0.2665
   1.750   0.8418   0.00660   0.00140  -0.1364   0.5920   0.3824
   2.000   0.8666   0.00654   0.00154  -0.1357   0.5719   0.5211
   2.250   0.8950   0.00585   0.00163  -0.1360   0.5476   1.0000
   2.500   0.9197   0.00608   0.00170  -0.1352   0.5149   1.0000
   2.750   0.9432   0.00643   0.00181  -0.1342   0.4682   1.0000
   3.000   0.9671   0.00676   0.00195  -0.1334   0.4310   1.0000
   3.250   0.9914   0.00706   0.00209  -0.1326   0.3993   1.0000
   3.500   1.0156   0.00740   0.00225  -0.1318   0.3652   1.0000
   3.750   1.0398   0.00772   0.00241  -0.1311   0.3349   1.0000
   4.000   1.0643   0.00801   0.00260  -0.1304   0.3099   1.0000
   4.250   1.0885   0.00832   0.00278  -0.1297   0.2845   1.0000
   4.500   1.1127   0.00864   0.00297  -0.1290   0.2591   1.0000
   4.750   1.1367   0.00898   0.00318  -0.1282   0.2331   1.0000
   5.000   1.1603   0.00935   0.00341  -0.1274   0.2072   1.0000
   5.250   1.1838   0.00973   0.00368  -0.1266   0.1825   1.0000
   5.500   1.2069   0.01014   0.00396  -0.1257   0.1595   1.0000
   5.750   1.2304   0.01051   0.00424  -0.1249   0.1397   1.0000
   6.000   1.2533   0.01093   0.00454  -0.1240   0.1208   1.0000
   6.250   1.2764   0.01132   0.00486  -0.1232   0.1054   1.0000
   6.500   1.2997   0.01169   0.00518  -0.1223   0.0937   1.0000
   6.750   1.3230   0.01204   0.00549  -0.1215   0.0847   1.0000
   7.000   1.3463   0.01240   0.00583  -0.1207   0.0770   1.0000
   7.250   1.3690   0.01280   0.00620  -0.1198   0.0706   1.0000
   7.500   1.3920   0.01316   0.00658  -0.1189   0.0663   1.0000
   7.750   1.4153   0.01347   0.00693  -0.1181   0.0637   1.0000
   8.000   1.4378   0.01386   0.00732  -0.1172   0.0606   1.0000
   8.250   1.4591   0.01437   0.00785  -0.1160   0.0569   1.0000
   8.500   1.4809   0.01480   0.00833  -0.1150   0.0550   1.0000
   8.750   1.5039   0.01508   0.00866  -0.1142   0.0538   1.0000
   9.000   1.5265   0.01538   0.00900  -0.1133   0.0517   1.0000
   9.250   1.5480   0.01578   0.00943  -0.1123   0.0498   1.0000
   9.500   1.5679   0.01633   0.00997  -0.1110   0.0458   1.0000
   9.750   1.5905   0.01657   0.01025  -0.1102   0.0435   1.0000
  10.000   1.6126   0.01685   0.01057  -0.1094   0.0415   1.0000
  10.250   1.6332   0.01725   0.01097  -0.1083   0.0388   1.0000
  10.500   1.6518   0.01782   0.01154  -0.1069   0.0346   1.0000
  10.750   1.6729   0.01812   0.01188  -0.1059   0.0313   1.0000
  11.000   1.6868   0.01904   0.01264  -0.1038   0.0190   1.0000
  11.250   1.6861   0.02113   0.01460  -0.0994   0.0030   1.0000
  11.500   1.6944   0.02219   0.01575  -0.0962   0.0017   1.0000
  11.750   1.7028   0.02320   0.01689  -0.0931   0.0012   1.0000
  12.000   1.7113   0.02420   0.01800  -0.0902   0.0010   1.0000
  12.250   1.7185   0.02529   0.01922  -0.0872   0.0009   1.0000
  12.500   1.7246   0.02649   0.02054  -0.0842   0.0008   1.0000
  12.750   1.7268   0.02804   0.02223  -0.0809   0.0007   1.0000
  13.000   1.7276   0.02973   0.02410  -0.0777   0.0007   1.0000
  13.250   1.7268   0.03160   0.02613  -0.0746   0.0007   1.0000
  13.500   1.7235   0.03378   0.02848  -0.0716   0.0007   1.0000
  13.750   1.7162   0.03646   0.03132  -0.0688   0.0006   1.0000
  14.000   1.7072   0.03950   0.03454  -0.0665   0.0006   1.0000
  14.250   1.6965   0.04297   0.03820  -0.0649   0.0006   1.0000
  14.500   1.6876   0.04654   0.04192  -0.0639   0.0006   1.0000
  14.750   1.6772   0.05059   0.04612  -0.0634   0.0006   1.0000
  15.000   1.6651   0.05519   0.05088  -0.0637   0.0006   1.0000
  15.250   1.6520   0.06024   0.05610  -0.0645   0.0006   1.0000
  15.500   1.6360   0.06615   0.06217  -0.0661   0.0006   1.0000
  15.750   1.6191   0.07262   0.06880  -0.0683   0.0006   1.0000
  16.000   1.5995   0.08010   0.07645  -0.0715   0.0006   1.0000
  16.250   1.5785   0.08843   0.08496  -0.0754   0.0006   1.0000
<< Back to S1091 (s1091-il)

Polar data table (+)

Polar graphs


<< Back to S1091 (s1091-il)