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St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: St. CYR 171 (Royer) (stcyr171-il)
Reynolds number: 50,000
Max Cl/Cd: 24.73 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stcyr171-il-50000.txt
Download as CSV file: xf-stcyr171-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: St. CYR 171 (Royer)                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6236   0.08533   0.07758  -0.0195   1.0000   0.1741
  -9.000  -0.6370   0.07942   0.07174  -0.0214   1.0000   0.1728
  -8.750  -0.6589   0.07330   0.06567  -0.0226   1.0000   0.1713
  -8.500  -0.6867   0.06613   0.05846  -0.0242   1.0000   0.1694
  -8.250  -0.7164   0.05871   0.05086  -0.0251   1.0000   0.1687
  -8.000  -0.7365   0.05250   0.04428  -0.0243   1.0000   0.1708
  -7.750  -0.7544   0.04689   0.03797  -0.0220   1.0000   0.1752
  -7.500  -0.7350   0.04549   0.03677  -0.0202   1.0000   0.1882
  -7.250  -0.7262   0.04285   0.03400  -0.0179   1.0000   0.2026
  -7.000  -0.7177   0.04027   0.03121  -0.0153   1.0000   0.2207
  -6.750  -0.7070   0.03823   0.02898  -0.0130   1.0000   0.2401
  -6.500  -0.6940   0.03646   0.02707  -0.0108   1.0000   0.2581
  -6.250  -0.6823   0.03473   0.02516  -0.0086   1.0000   0.2776
  -6.000  -0.6643   0.03382   0.02444  -0.0065   1.0000   0.2961
  -5.750  -0.6437   0.03389   0.02473  -0.0042   1.0000   0.3121
  -5.500  -0.6194   0.03473   0.02575  -0.0020   1.0000   0.3233
  -5.250  -0.5999   0.03395   0.02492  -0.0002   1.0000   0.3297
  -5.000  -0.5786   0.03376   0.02469   0.0015   1.0000   0.3374
  -4.750  -0.5573   0.03364   0.02456   0.0033   1.0000   0.3446
  -4.500  -0.5374   0.03310   0.02394   0.0049   1.0000   0.3523
  -4.250  -0.5163   0.03285   0.02367   0.0065   1.0000   0.3589
  -4.000  -0.4966   0.03238   0.02314   0.0080   1.0000   0.3680
  -3.750  -0.4762   0.03229   0.02301   0.0097   1.0000   0.3791
  -3.500  -0.4562   0.03218   0.02284   0.0113   1.0000   0.3912
  -3.250  -0.4370   0.03199   0.02255   0.0129   1.0000   0.4048
  -3.000  -0.4192   0.03196   0.02232   0.0144   1.0000   0.4219
  -2.750  -0.4030   0.03151   0.02179   0.0164   1.0000   0.4403
  -2.500  -0.3901   0.03064   0.02070   0.0185   1.0000   0.4650
  -2.250  -0.3808   0.02814   0.01801   0.0207   1.0000   0.4981
  -2.000  -0.3720   0.02361   0.01318   0.0225   1.0000   0.5474
  -1.750  -0.3320   0.01935   0.00962   0.0200   1.0000   0.6054
  -1.500  -0.3162   0.01916   0.01010   0.0235   1.0000   0.6432
  -1.250  -0.3027   0.01924   0.01016   0.0261   1.0000   0.6853
  -1.000  -0.2878   0.01919   0.01010   0.0282   1.0000   0.7194
  -0.750  -0.2694   0.01907   0.01010   0.0299   1.0000   0.7482
  -0.500  -0.2490   0.01901   0.01018   0.0310   1.0000   0.7752
  -0.250  -0.2238   0.01904   0.01042   0.0314   1.0000   0.8061
   0.000  -0.1901   0.01924   0.01079   0.0299   1.0000   0.8434
   0.250  -0.1430   0.01959   0.01130   0.0255   1.0000   0.8889
   0.500  -0.0902   0.02003   0.01181   0.0195   1.0000   0.9350
   0.750  -0.0400   0.02050   0.01232   0.0134   1.0000   0.9860
   1.000  -0.0300   0.02089   0.01260   0.0140   1.0000   1.0000
   1.250  -0.0243   0.02129   0.01291   0.0156   1.0000   1.0000
   1.500   0.0565   0.02229   0.01400   0.0040   0.9734   1.0000
   1.750   0.1480   0.02275   0.01462  -0.0082   0.9393   1.0000
   2.000   0.2443   0.02245   0.01457  -0.0197   0.9028   1.0000
   2.250   0.3483   0.02115   0.01361  -0.0304   0.8578   1.0000
   2.500   0.4172   0.01981   0.01243  -0.0337   0.7961   1.0000
   2.750   0.4530   0.01925   0.01167  -0.0312   0.7125   1.0000
   3.000   0.4683   0.01945   0.01140  -0.0263   0.6114   1.0000
   3.250   0.4872   0.02007   0.01135  -0.0231   0.5326   1.0000
   3.500   0.5087   0.02094   0.01187  -0.0214   0.4807   1.0000
   3.750   0.5306   0.02174   0.01248  -0.0200   0.4460   1.0000
   4.000   0.5538   0.02253   0.01304  -0.0188   0.4210   1.0000
   4.250   0.5772   0.02340   0.01385  -0.0178   0.4017   1.0000
   4.500   0.6012   0.02431   0.01467  -0.0169   0.3858   1.0000
   4.750   0.6239   0.02528   0.01568  -0.0158   0.3709   1.0000
   5.000   0.6460   0.02639   0.01690  -0.0148   0.3582   1.0000
   5.250   0.6697   0.02763   0.01813  -0.0139   0.3487   1.0000
   5.500   0.6905   0.02893   0.01965  -0.0127   0.3384   1.0000
   5.750   0.7113   0.03036   0.02117  -0.0116   0.3286   1.0000
   6.000   0.7312   0.03189   0.02288  -0.0103   0.3195   1.0000
   6.250   0.7486   0.03356   0.02474  -0.0087   0.3090   1.0000
   6.500   0.7665   0.03477   0.02596  -0.0070   0.2922   1.0000
   6.750   0.7822   0.03575   0.02696  -0.0049   0.2714   1.0000
   7.000   0.7979   0.03686   0.02810  -0.0029   0.2517   1.0000
   7.250   0.8124   0.03859   0.02995  -0.0009   0.2349   1.0000
   7.500   0.8245   0.04062   0.03212   0.0014   0.2170   1.0000
   7.750   0.8346   0.04289   0.03452   0.0038   0.1996   1.0000
   8.000   0.8480   0.04532   0.03697   0.0058   0.1860   1.0000
   8.250   0.8438   0.04906   0.04124   0.0088   0.1783   1.0000
   8.500   0.8622   0.05142   0.04346   0.0100   0.1698   1.0000
   8.750   0.8468   0.05594   0.04853   0.0130   0.1669   1.0000
   9.000   0.8285   0.06074   0.05368   0.0152   0.1651   1.0000
   9.250   0.8047   0.06601   0.05919   0.0167   0.1652   1.0000
   9.500   0.7755   0.07170   0.06500   0.0174   0.1665   1.0000
   9.750   0.7477   0.07746   0.07078   0.0173   0.1681   1.0000
  10.000   0.7270   0.08392   0.07723   0.0153   0.1695   1.0000
  10.250   0.7162   0.09043   0.08375   0.0128   0.1711   1.0000
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