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S1091 (s1091-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 50,000
Max Cl/Cd: 48.34 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1091-il-50000-n5.txt
Download as CSV file: xf-s1091-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2871   0.10468   0.09808  -0.0198   1.0000   0.0627
  -6.750  -0.2877   0.10292   0.09638  -0.0189   1.0000   0.0642
  -6.500  -0.2866   0.10107   0.09464  -0.0188   1.0000   0.0660
  -6.250  -0.2850   0.09968   0.09335  -0.0196   1.0000   0.0677
  -6.000  -0.2820   0.09889   0.09267  -0.0220   1.0000   0.0688
  -5.750  -0.2750   0.09817   0.09202  -0.0257   1.0000   0.0694
  -5.500  -0.2666   0.09606   0.09002  -0.0282   1.0000   0.0699
  -5.250  -0.2673   0.09088   0.08492  -0.0227   1.0000   0.0712
  -5.000  -0.2636   0.08786   0.08197  -0.0209   1.0000   0.0730
  -4.750  -0.2582   0.08543   0.07962  -0.0206   1.0000   0.0750
  -4.500  -0.2511   0.08318   0.07742  -0.0213   1.0000   0.0776
  -4.250  -0.2395   0.08116   0.07544  -0.0238   1.0000   0.0811
  -3.750  -0.2086   0.07635   0.07069  -0.0305   1.0000   0.0855
  -3.500  -0.2010   0.07332   0.06772  -0.0290   0.9989   0.0894
  -3.250  -0.1432   0.07000   0.06422  -0.0428   0.9917   0.0992
  -3.000  -0.1206   0.06603   0.06028  -0.0438   0.9854   0.1051
  -2.500  -0.0212   0.05938   0.05335  -0.0624   0.9721   0.1259
  -2.250   0.0138   0.05557   0.04951  -0.0668   0.9645   0.1295
  -2.000   0.0895   0.04972   0.04316  -0.0798   0.9603   0.0684
  -1.750   0.1348   0.04551   0.03872  -0.0855   0.9538   0.0533
  -1.500   0.1855   0.04172   0.03467  -0.0921   0.9481   0.0485
  -1.250   0.2359   0.03828   0.03087  -0.0981   0.9418   0.0477
  -1.000   0.2849   0.03536   0.02755  -0.1033   0.9354   0.0501
  -0.750   0.3325   0.03249   0.02413  -0.1076   0.9288   0.0501
  -0.500   0.3781   0.03003   0.02106  -0.1110   0.9221   0.0505
  -0.250   0.4195   0.02815   0.01854  -0.1132   0.9142   0.0539
   0.000   0.4621   0.02678   0.01675  -0.1157   0.9070   0.0616
   0.250   0.5006   0.02570   0.01512  -0.1170   0.8975   0.0680
   0.500   0.5429   0.02473   0.01393  -0.1191   0.8898   0.0868
   0.750   0.5815   0.02384   0.01316  -0.1206   0.8801   0.1539
   1.000   0.6172   0.02292   0.01296  -0.1220   0.8696   0.3505
   1.250   0.6521   0.02143   0.01230  -0.1227   0.8591   1.0000
   1.500   0.6920   0.02136   0.01176  -0.1242   0.8487   1.0000
   1.750   0.7260   0.02137   0.01150  -0.1248   0.8358   1.0000
   2.000   0.7592   0.02140   0.01131  -0.1252   0.8223   1.0000
   2.250   0.7923   0.02142   0.01117  -0.1255   0.8085   1.0000
   2.500   0.8250   0.02144   0.01106  -0.1257   0.7940   1.0000
   2.750   0.8573   0.02146   0.01099  -0.1258   0.7790   1.0000
   3.000   0.8895   0.02148   0.01093  -0.1258   0.7632   1.0000
   3.250   0.9170   0.02163   0.01108  -0.1251   0.7447   1.0000
   3.500   0.9455   0.02174   0.01115  -0.1244   0.7256   1.0000
   3.750   0.9755   0.02178   0.01114  -0.1238   0.7060   1.0000
   4.000   1.0004   0.02198   0.01133  -0.1226   0.6828   1.0000
   4.250   1.0266   0.02212   0.01143  -0.1214   0.6590   1.0000
   4.500   1.0518   0.02228   0.01163  -0.1200   0.6329   1.0000
   4.750   1.0747   0.02252   0.01184  -0.1184   0.6041   1.0000
   5.000   1.0960   0.02281   0.01211  -0.1165   0.5723   1.0000
   5.250   1.1168   0.02314   0.01240  -0.1146   0.5378   1.0000
   5.500   1.1369   0.02352   0.01269  -0.1126   0.5008   1.0000
   5.750   1.1565   0.02401   0.01310  -0.1106   0.4622   1.0000
   6.000   1.1747   0.02467   0.01361  -0.1085   0.4224   1.0000
   6.250   1.1921   0.02548   0.01425  -0.1065   0.3833   1.0000
   6.500   1.2084   0.02642   0.01502  -0.1045   0.3454   1.0000
   6.750   1.2242   0.02745   0.01594  -0.1026   0.3092   1.0000
   7.250   1.2537   0.02982   0.01812  -0.0987   0.2456   1.0000
   7.500   1.2681   0.03111   0.01932  -0.0968   0.2198   1.0000
   7.750   1.2835   0.03245   0.02064  -0.0951   0.1983   1.0000
   8.000   1.2994   0.03386   0.02204  -0.0935   0.1821   1.0000
   8.250   1.3156   0.03529   0.02354  -0.0919   0.1682   1.0000
   8.500   1.3319   0.03673   0.02505  -0.0904   0.1560   1.0000
   8.750   1.3487   0.03822   0.02659  -0.0890   0.1460   1.0000
   9.000   1.3676   0.03976   0.02823  -0.0878   0.1384   1.0000
   9.250   1.3889   0.04146   0.03014  -0.0869   0.1320   1.0000
   9.500   1.4098   0.04322   0.03213  -0.0860   0.1265   1.0000
   9.750   1.4306   0.04509   0.03411  -0.0853   0.1215   1.0000
  10.000   1.4461   0.04707   0.03648  -0.0838   0.1160   1.0000
  10.250   1.4625   0.04889   0.03843  -0.0827   0.1113   1.0000
  10.500   1.4795   0.05128   0.04109  -0.0816   0.1080   1.0000
  10.750   1.4905   0.05403   0.04434  -0.0799   0.1051   1.0000
  11.000   1.4997   0.05689   0.04766  -0.0782   0.1026   1.0000
  11.250   1.5073   0.05973   0.05084  -0.0764   0.1003   1.0000
  11.500   1.5179   0.06225   0.05353  -0.0750   0.0976   1.0000
  11.750   1.5149   0.06537   0.05697  -0.0724   0.0955   1.0000
  12.000   1.4981   0.06888   0.06092  -0.0689   0.0940   1.0000
  12.250   1.4793   0.07277   0.06518  -0.0662   0.0927   1.0000
  12.500   1.4581   0.07722   0.06995  -0.0644   0.0918   1.0000
  12.750   1.4334   0.08248   0.07551  -0.0637   0.0912   1.0000
  13.000   1.4033   0.08898   0.08226  -0.0647   0.0911   1.0000
  13.250   1.3656   0.09747   0.09097  -0.0679   0.0916   1.0000
  13.500   1.3196   0.10904   0.10265  -0.0743   0.0929   1.0000
  13.750   1.2695   0.12416   0.11773  -0.0841   0.0943   1.0000
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