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S1091 (s1091-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.69 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1091-il-1000000-n5.txt
Download as CSV file: xf-s1091-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1585   0.08529   0.08371  -0.0420   0.9895   0.0042
  -8.250  -0.1482   0.08201   0.08043  -0.0438   0.9883   0.0043
  -8.000  -0.1371   0.07856   0.07698  -0.0459   0.9870   0.0044
  -7.750  -0.1254   0.07513   0.07356  -0.0481   0.9859   0.0045
  -7.500  -0.1130   0.07157   0.07001  -0.0506   0.9848   0.0046
  -7.250  -0.1080   0.06881   0.06725  -0.0509   0.9806   0.0046
  -7.000  -0.0979   0.06559   0.06405  -0.0527   0.9773   0.0047
  -6.750  -0.0853   0.06214   0.06060  -0.0552   0.9744   0.0047
  -6.500  -0.0781   0.05924   0.05771  -0.0562   0.9681   0.0047
  -6.000  -0.0575   0.05306   0.05154  -0.0600   0.9510   0.0048
  -5.750  -0.0369   0.04920   0.04767  -0.0647   0.9422   0.0050
  -5.500  -0.0056   0.04465   0.04308  -0.0721   0.9335   0.0050
  -5.250   0.0316   0.03983   0.03821  -0.0810   0.9194   0.0052
  -5.000   0.0657   0.03560   0.03384  -0.0885   0.8908   0.0055
  -4.750   0.0869   0.03252   0.03059  -0.0922   0.8534   0.0057
  -4.500   0.1058   0.02979   0.02771  -0.0949   0.8213   0.0059
  -4.250   0.1277   0.02695   0.02474  -0.0982   0.7963   0.0061
  -4.000   0.1532   0.02395   0.02162  -0.1023   0.7749   0.0062
  -3.750   0.1797   0.02105   0.01861  -0.1060   0.7557   0.0062
  -3.500   0.2077   0.01829   0.01572  -0.1097   0.7370   0.0062
  -3.250   0.2386   0.01549   0.01280  -0.1137   0.7232   0.0062
  -3.000   0.2715   0.01279   0.00996  -0.1180   0.7098   0.0062
  -2.750   0.3351   0.02542   0.02224  -0.1356   0.7311   0.0038
  -2.500   0.3731   0.02049   0.01698  -0.1393   0.7172   0.0037
  -2.250   0.4119   0.01197   0.00749  -0.1419   0.7067   0.0037
  -2.000   0.4396   0.00972   0.00463  -0.1416   0.6938   0.0042
  -1.750   0.4661   0.00933   0.00408  -0.1412   0.6814   0.0045
  -1.500   0.4927   0.00900   0.00359  -0.1408   0.6696   0.0050
  -1.250   0.5193   0.00861   0.00304  -0.1403   0.6586   0.0053
  -1.000   0.5460   0.00834   0.00265  -0.1398   0.6479   0.0058
  -0.750   0.5728   0.00828   0.00252  -0.1394   0.6376   0.0063
  -0.500   0.5994   0.00787   0.00199  -0.1389   0.6267   0.0065
  -0.250   0.6259   0.00766   0.00168  -0.1384   0.6155   0.0066
   0.000   0.6524   0.00752   0.00145  -0.1379   0.6025   0.0069
   0.250   0.6788   0.00746   0.00131  -0.1374   0.5881   0.0076
   0.500   0.7051   0.00745   0.00121  -0.1369   0.5723   0.0096
   0.750   0.7313   0.00745   0.00115  -0.1364   0.5533   0.0170
   1.000   0.7567   0.00740   0.00117  -0.1358   0.5279   0.0790
   1.250   0.7814   0.00753   0.00123  -0.1351   0.4908   0.1215
   1.500   0.8059   0.00770   0.00133  -0.1344   0.4547   0.1668
   1.750   0.8303   0.00786   0.00146  -0.1337   0.4183   0.2321
   2.000   0.8548   0.00809   0.00159  -0.1330   0.3841   0.2680
   2.250   0.8797   0.00828   0.00172  -0.1323   0.3556   0.3081
   2.500   0.9043   0.00848   0.00188  -0.1317   0.3263   0.3602
   2.750   0.9287   0.00870   0.00206  -0.1310   0.2947   0.4180
   3.000   0.9533   0.00889   0.00224  -0.1304   0.2694   0.4815
   3.250   0.9718   0.00833   0.00243  -0.1285   0.2523   0.8913
   3.500   1.0051   0.00854   0.00259  -0.1298   0.2262   1.0000
   3.750   1.0292   0.00888   0.00279  -0.1291   0.1984   1.0000
   4.000   1.0537   0.00918   0.00298  -0.1284   0.1770   1.0000
   4.250   1.0781   0.00949   0.00317  -0.1277   0.1589   1.0000
   4.500   1.1026   0.00977   0.00337  -0.1270   0.1431   1.0000
   4.750   1.1270   0.01006   0.00358  -0.1263   0.1289   1.0000
   5.000   1.1514   0.01035   0.00382  -0.1257   0.1161   1.0000
   5.250   1.1757   0.01065   0.00405  -0.1250   0.1048   1.0000
   5.500   1.2001   0.01092   0.00427  -0.1243   0.0956   1.0000
   5.750   1.2244   0.01120   0.00451  -0.1236   0.0875   1.0000
   6.000   1.2481   0.01153   0.00480  -0.1229   0.0782   1.0000
   6.250   1.2724   0.01180   0.00505  -0.1222   0.0726   1.0000
   6.500   1.2960   0.01212   0.00534  -0.1214   0.0663   1.0000
   6.750   1.3202   0.01238   0.00560  -0.1208   0.0632   1.0000
   7.000   1.3439   0.01268   0.00591  -0.1200   0.0595   1.0000
   7.250   1.3672   0.01301   0.00623  -0.1192   0.0557   1.0000
   7.500   1.3909   0.01329   0.00654  -0.1185   0.0537   1.0000
   7.750   1.4144   0.01358   0.00685  -0.1177   0.0522   1.0000
   8.000   1.4375   0.01389   0.00720  -0.1169   0.0506   1.0000
   8.250   1.4603   0.01423   0.00757  -0.1161   0.0488   1.0000
   8.500   1.4826   0.01460   0.00796  -0.1151   0.0470   1.0000
   8.750   1.5045   0.01501   0.00839  -0.1141   0.0448   1.0000
   9.000   1.5267   0.01536   0.00879  -0.1132   0.0433   1.0000
   9.250   1.5491   0.01566   0.00915  -0.1124   0.0420   1.0000
   9.500   1.5708   0.01603   0.00954  -0.1114   0.0394   1.0000
   9.750   1.5911   0.01651   0.00999  -0.1102   0.0354   1.0000
  10.000   1.6119   0.01691   0.01044  -0.1091   0.0333   1.0000
  10.250   1.6323   0.01734   0.01089  -0.1080   0.0301   1.0000
  10.500   1.6506   0.01793   0.01146  -0.1066   0.0254   1.0000
  10.750   1.6668   0.01868   0.01217  -0.1048   0.0179   1.0000
  11.000   1.6766   0.01996   0.01339  -0.1021   0.0078   1.0000
  11.250   1.6852   0.02120   0.01465  -0.0991   0.0024   1.0000
  11.500   1.6949   0.02215   0.01567  -0.0962   0.0011   1.0000
  11.750   1.7049   0.02304   0.01665  -0.0934   0.0007   1.0000
  12.000   1.7151   0.02388   0.01759  -0.0907   0.0006   1.0000
  12.250   1.7244   0.02480   0.01861  -0.0880   0.0005   1.0000
  12.500   1.7321   0.02585   0.01977  -0.0853   0.0004   1.0000
  12.750   1.7381   0.02705   0.02111  -0.0824   0.0003   1.0000
  13.000   1.7429   0.02839   0.02257  -0.0795   0.0002   1.0000
  13.250   1.7497   0.02957   0.02385  -0.0771   0.0002   1.0000
  13.500   1.7547   0.03094   0.02533  -0.0747   0.0002   1.0000
  13.750   1.7589   0.03244   0.02694  -0.0724   0.0002   1.0000
  14.000   1.7613   0.03417   0.02880  -0.0702   0.0002   1.0000
  14.250   1.7620   0.03615   0.03091  -0.0682   0.0002   1.0000
  14.500   1.7623   0.03826   0.03315  -0.0664   0.0002   1.0000
  14.750   1.7605   0.04073   0.03575  -0.0649   0.0002   1.0000
  15.000   1.7580   0.04342   0.03858  -0.0637   0.0002   1.0000
  15.250   1.7540   0.04645   0.04174  -0.0628   0.0001   1.0000
  15.500   1.7477   0.04996   0.04540  -0.0624   0.0001   1.0000
  15.750   1.7409   0.05370   0.04929  -0.0623   0.0001   1.0000
  16.000   1.7306   0.05818   0.05392  -0.0627   0.0001   1.0000
  16.250   1.7206   0.06287   0.05877  -0.0636   0.0001   1.0000
  16.500   1.7083   0.06818   0.06423  -0.0650   0.0001   1.0000
  16.750   1.6922   0.07446   0.07068  -0.0672   0.0001   1.0000
  17.000   1.6746   0.08143   0.07782  -0.0700   0.0001   1.0000
  17.250   1.6560   0.08902   0.08557  -0.0735   0.0001   1.0000
  17.500   1.6317   0.09822   0.09495  -0.0782   0.0001   1.0000
  17.750   1.6070   0.10795   0.10486  -0.0833   0.0001   1.0000
  18.000   1.5775   0.11912   0.11619  -0.0895   0.0001   1.0000
  18.250   1.5452   0.13135   0.12860  -0.0966   0.0001   1.0000
  18.500   1.5116   0.14424   0.14167  -0.1042   0.0001   1.0000
  18.750   1.4772   0.15779   0.15538  -0.1124   0.0002   1.0000
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