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S1091 (s1091-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 50,000
Max Cl/Cd: 46.09 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1091-il-50000.txt
Download as CSV file: xf-s1091-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3007   0.11553   0.10864  -0.0219   1.0000   0.0908
  -7.750  -0.3066   0.11570   0.10894  -0.0218   1.0000   0.0918
  -7.500  -0.3145   0.11619   0.10958  -0.0217   1.0000   0.0922
  -7.250  -0.3127   0.11393   0.10745  -0.0222   1.0000   0.0929
  -7.000  -0.2942   0.10602   0.09951  -0.0191   1.0000   0.0967
  -6.750  -0.2927   0.10374   0.09731  -0.0180   1.0000   0.0996
  -6.500  -0.2917   0.10193   0.09560  -0.0178   1.0000   0.1027
  -6.250  -0.2913   0.10097   0.09475  -0.0187   1.0000   0.1052
  -6.000  -0.2898   0.10165   0.09554  -0.0230   1.0000   0.1067
  -5.750  -0.2856   0.09704   0.09101  -0.0206   1.0000   0.1083
  -5.500  -0.2810   0.09319   0.08722  -0.0176   1.0000   0.1120
  -5.250  -0.2768   0.09107   0.08518  -0.0176   1.0000   0.1164
  -5.000  -0.2673   0.09100   0.08517  -0.0230   1.0000   0.1208
  -4.750  -0.2636   0.08748   0.08175  -0.0217   1.0000   0.1231
  -4.500  -0.2610   0.08431   0.07866  -0.0188   1.0000   0.1279
  -4.250  -0.2424   0.08389   0.07823  -0.0258   1.0000   0.1354
  -4.000  -0.2406   0.08014   0.07458  -0.0231   1.0000   0.1383
  -3.750  -0.2347   0.07748   0.07199  -0.0219   1.0000   0.1447
  -3.500  -0.2147   0.07550   0.07001  -0.0271   1.0000   0.1520
  -3.250  -0.2093   0.07261   0.06719  -0.0251   1.0000   0.1583
  -3.000  -0.1872   0.07033   0.06486  -0.0297   1.0000   0.1671
  -2.750  -0.1600   0.06839   0.06287  -0.0351   1.0000   0.1798
  -2.500  -0.1565   0.06510   0.05968  -0.0320   1.0000   0.1864
  -2.250  -0.1348   0.06255   0.05712  -0.0348   1.0000   0.1993
  -2.000  -0.1124   0.06009   0.05465  -0.0374   1.0000   0.2141
  -1.750  -0.0789   0.05811   0.05259  -0.0430   1.0000   0.2376
  -1.500  -0.0625   0.05530   0.04981  -0.0430   1.0000   0.2548
  -1.250  -0.0373   0.05307   0.04754  -0.0454   1.0000   0.2824
  -1.000  -0.0181   0.05068   0.04518  -0.0458   1.0000   0.3141
  -0.750  -0.0004   0.04847   0.04302  -0.0457   1.0000   0.3585
   0.500   0.2700   0.03739   0.02968  -0.0842   1.0000   0.1475
   0.750   0.3031   0.03598   0.02788  -0.0861   1.0000   0.1405
   1.000   0.3362   0.03500   0.02627  -0.0876   1.0000   0.1352
   1.250   0.3965   0.03384   0.02449  -0.0935   0.9893   0.1373
   1.500   0.4545   0.03340   0.02351  -0.0988   0.9767   0.1656
   1.750   0.5091   0.03258   0.02295  -0.1034   0.9642   0.3006
   2.000   0.5592   0.03072   0.02198  -0.1071   0.9506   1.0000
   2.250   0.6092   0.03157   0.02226  -0.1116   0.9338   1.0000
   2.500   0.6515   0.03226   0.02266  -0.1148   0.9150   1.0000
   2.750   0.6955   0.03283   0.02303  -0.1179   0.8959   1.0000
   3.000   0.7466   0.03316   0.02322  -0.1218   0.8778   1.0000
   3.250   0.7834   0.03356   0.02357  -0.1233   0.8564   1.0000
   3.500   0.8333   0.03349   0.02349  -0.1262   0.8367   1.0000
   3.750   0.8780   0.03333   0.02340  -0.1279   0.8155   1.0000
   4.000   0.9324   0.03249   0.02263  -0.1303   0.7944   1.0000
   4.250   0.9819   0.03157   0.02181  -0.1315   0.7718   1.0000
   4.500   1.0369   0.03003   0.02045  -0.1326   0.7487   1.0000
   4.750   1.0775   0.02905   0.01955  -0.1318   0.7209   1.0000
   5.000   1.1171   0.02800   0.01854  -0.1305   0.6906   1.0000
   5.250   1.1458   0.02755   0.01811  -0.1281   0.6559   1.0000
   5.500   1.1756   0.02697   0.01756  -0.1257   0.6189   1.0000
   5.750   1.1987   0.02678   0.01731  -0.1227   0.5778   1.0000
   6.000   1.2204   0.02668   0.01707  -0.1196   0.5332   1.0000
   6.250   1.2394   0.02689   0.01705  -0.1163   0.4843   1.0000
   6.500   1.2572   0.02760   0.01745  -0.1132   0.4321   1.0000
   6.750   1.2733   0.02887   0.01838  -0.1104   0.3805   1.0000
   7.000   1.2905   0.03045   0.01965  -0.1080   0.3358   1.0000
   7.250   1.3100   0.03211   0.02096  -0.1062   0.2999   1.0000
   7.500   1.3307   0.03390   0.02258  -0.1048   0.2718   1.0000
   7.750   1.3514   0.03597   0.02487  -0.1034   0.2510   1.0000
   8.000   1.3733   0.03800   0.02696  -0.1023   0.2344   1.0000
   8.250   1.3936   0.04003   0.02909  -0.1010   0.2201   1.0000
   8.500   1.4136   0.04239   0.03166  -0.0998   0.2094   1.0000
   8.750   1.4389   0.04495   0.03422  -0.0994   0.2014   1.0000
   9.000   1.4495   0.04814   0.03813  -0.0971   0.1961   1.0000
   9.250   1.4648   0.05123   0.04156  -0.0955   0.1911   1.0000
   9.500   1.4799   0.05443   0.04499  -0.0942   0.1859   1.0000
   9.750   1.4784   0.05820   0.04940  -0.0911   0.1818   1.0000
  10.000   1.4826   0.06175   0.05332  -0.0889   0.1777   1.0000
  10.250   1.4880   0.06576   0.05765  -0.0870   0.1754   1.0000
  10.500   1.5002   0.07022   0.06226  -0.0860   0.1734   1.0000
  10.750   1.4866   0.07545   0.06793  -0.0832   0.1733   1.0000
  11.000   1.4017   0.08285   0.07593  -0.0775   0.1780   1.0000
  11.250   1.3345   0.09147   0.08466  -0.0767   0.1819   1.0000
  11.500   1.2874   0.10166   0.09487  -0.0802   0.1850   1.0000
  11.750   1.2669   0.11056   0.10379  -0.0835   0.1870   1.0000
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