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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 50,000
Max Cl/Cd: 38.08 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e174-il-50000.txt
Download as CSV file: xf-e174-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E174  (Dicke 8.92%)                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3685   0.11520   0.10854  -0.0238   1.0000   0.1659
  -8.750  -0.3473   0.10918   0.10252  -0.0225   1.0000   0.1719
  -8.500  -0.3502   0.10750   0.10095  -0.0240   1.0000   0.1793
  -8.250  -0.3443   0.10390   0.09742  -0.0244   1.0000   0.1838
  -8.000  -0.3379   0.10106   0.09464  -0.0244   1.0000   0.1924
  -7.750  -0.3416   0.09869   0.09240  -0.0254   1.0000   0.1976
  -7.500  -0.3350   0.09582   0.08960  -0.0249   1.0000   0.2075
  -7.250  -0.3309   0.09263   0.08648  -0.0244   1.0000   0.2151
  -7.000  -0.3428   0.09169   0.08572  -0.0243   1.0000   0.2234
  -6.750  -0.3335   0.08814   0.08225  -0.0226   1.0000   0.2346
  -6.500  -0.3389   0.08596   0.08023  -0.0217   1.0000   0.2436
  -6.250  -0.3556   0.08544   0.07991  -0.0218   1.0000   0.2535
  -6.000  -0.3517   0.08250   0.07707  -0.0181   1.0000   0.2657
  -5.750  -0.3630   0.08088   0.07560  -0.0154   1.0000   0.2731
  -5.500  -0.3850   0.08076   0.07561  -0.0137   1.0000   0.2827
  -5.250  -0.3871   0.07841   0.07336  -0.0092   1.0000   0.2938
  -5.000  -0.3966   0.07678   0.07182  -0.0067   1.0000   0.3044
  -4.750  -0.4045   0.07512   0.07024  -0.0044   1.0000   0.3185
  -4.500  -0.4093   0.07327   0.06846  -0.0020   1.0000   0.3354
  -4.250  -0.4162   0.07166   0.06690  -0.0015   1.0000   0.3586
  -4.000  -0.4154   0.06928   0.06459   0.0027   1.0000   0.3774
  -3.750  -0.4173   0.06728   0.06265   0.0055   1.0000   0.4051
  -3.000  -0.2254   0.04164   0.03381  -0.0529   1.0000   0.1229
  -2.750  -0.2022   0.03875   0.03080  -0.0536   1.0000   0.1183
  -2.500  -0.1740   0.03620   0.02769  -0.0548   1.0000   0.1161
  -2.250  -0.1325   0.03392   0.02476  -0.0579   0.9953   0.1189
  -2.000  -0.0869   0.03194   0.02200  -0.0610   0.9882   0.1226
  -1.750  -0.0451   0.03048   0.02024  -0.0638   0.9808   0.1370
  -1.500  -0.0053   0.02914   0.01890  -0.0661   0.9736   0.1704
  -1.250   0.0349   0.02760   0.01775  -0.0683   0.9668   0.2805
  -1.000   0.0689   0.02416   0.01662  -0.0673   0.9605   1.0000
  -0.750   0.1042   0.02489   0.01663  -0.0696   0.9516   1.0000
  -0.500   0.1457   0.02574   0.01691  -0.0730   0.9433   1.0000
  -0.250   0.1726   0.02642   0.01723  -0.0739   0.9340   1.0000
   0.000   0.2073   0.02725   0.01772  -0.0762   0.9257   1.0000
   0.250   0.2381   0.02804   0.01824  -0.0778   0.9169   1.0000
   0.500   0.2655   0.02886   0.01880  -0.0788   0.9085   1.0000
   0.750   0.3010   0.02974   0.01947  -0.0811   0.9004   1.0000
   1.000   0.3217   0.03058   0.02016  -0.0810   0.8917   1.0000
   1.250   0.3570   0.03153   0.02094  -0.0832   0.8839   1.0000
   1.500   0.3762   0.03243   0.02174  -0.0830   0.8751   1.0000
   1.750   0.4044   0.03342   0.02263  -0.0841   0.8673   1.0000
   2.000   0.4300   0.03440   0.02353  -0.0848   0.8586   1.0000
   2.250   0.4508   0.03547   0.02454  -0.0849   0.8504   1.0000
   2.500   0.4846   0.03649   0.02553  -0.0867   0.8420   1.0000
   2.750   0.4976   0.03765   0.02666  -0.0857   0.8331   1.0000
   3.000   0.5272   0.03877   0.02779  -0.0869   0.8245   1.0000
   3.250   0.5481   0.03993   0.02895  -0.0869   0.8150   1.0000
   3.500   0.5660   0.04120   0.03023  -0.0866   0.8056   1.0000
   3.750   0.5974   0.04234   0.03142  -0.0879   0.7959   1.0000
   4.000   0.6172   0.04359   0.03272  -0.0877   0.7854   1.0000
   4.250   0.6335   0.04495   0.03416  -0.0872   0.7743   1.0000
   4.500   0.6562   0.04625   0.03553  -0.0873   0.7628   1.0000
   4.750   0.6830   0.04745   0.03683  -0.0878   0.7507   1.0000
   5.000   0.7109   0.04860   0.03810  -0.0881   0.7375   1.0000
   5.250   0.7377   0.04972   0.03940  -0.0883   0.7237   1.0000
   5.500   0.7610   0.05090   0.04071  -0.0880   0.7090   1.0000
   5.750   0.7801   0.05216   0.04211  -0.0873   0.6931   1.0000
   6.000   0.7997   0.05339   0.04350  -0.0865   0.6763   1.0000
   6.250   0.8249   0.05432   0.04461  -0.0859   0.6585   1.0000
   6.500   0.8670   0.05421   0.04484  -0.0858   0.6399   1.0000
   6.750   0.8894   0.05496   0.04580  -0.0844   0.6200   1.0000
   7.000   0.9256   0.05451   0.04566  -0.0832   0.5985   1.0000
   7.250   0.9669   0.05320   0.04476  -0.0814   0.5760   1.0000
   7.500   1.0677   0.04485   0.03716  -0.0783   0.5522   1.0000
   7.750   1.1153   0.04058   0.03332  -0.0743   0.5210   1.0000
   8.000   1.1651   0.03496   0.02803  -0.0694   0.4758   1.0000
   8.250   1.1910   0.03128   0.02433  -0.0636   0.4065   1.0000
   8.500   1.1887   0.03132   0.02369  -0.0576   0.3188   1.0000
   8.750   1.1764   0.03370   0.02522  -0.0526   0.2474   1.0000
   9.000   1.1636   0.03673   0.02762  -0.0484   0.1942   1.0000
   9.250   1.1582   0.03995   0.03035  -0.0449   0.1519   1.0000
   9.500   1.1837   0.04352   0.03351  -0.0435   0.1153   1.0000
   9.750   1.2164   0.04671   0.03667  -0.0433   0.0973   1.0000
  10.000   1.2527   0.05081   0.04102  -0.0434   0.0897   1.0000
  10.250   1.2730   0.05474   0.04543  -0.0424   0.0863   1.0000
  10.500   1.2894   0.05878   0.04978  -0.0414   0.0838   1.0000
  10.750   1.3079   0.06399   0.05505  -0.0412   0.0810   1.0000
  11.000   1.3020   0.06774   0.05930  -0.0388   0.0804   1.0000
  11.250   1.2927   0.07168   0.06367  -0.0365   0.0801   1.0000
  11.500   1.2797   0.07563   0.06795  -0.0343   0.0801   1.0000
  11.750   1.2642   0.07970   0.07229  -0.0325   0.0802   1.0000
  12.000   1.2470   0.08412   0.07693  -0.0314   0.0805   1.0000
  12.250   1.2313   0.08908   0.08209  -0.0312   0.0808   1.0000
  12.500   1.1450   0.09761   0.09121  -0.0363   0.0880   1.0000
  12.750   1.1154   0.10570   0.09938  -0.0405   0.0901   1.0000
  13.000   1.0928   0.11393   0.10766  -0.0447   0.0918   1.0000
  13.250   1.0796   0.12163   0.11539  -0.0482   0.0930   1.0000
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