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St. CYR 172 (Royer) (stcyr172-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: St. CYR 172 (Royer) (stcyr172-il)
Reynolds number: 100,000
Max Cl/Cd: 37.69 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stcyr172-il-100000.txt
Download as CSV file: xf-stcyr172-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: St. CYR 172 (Royer)                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.8820   0.07696   0.07077  -0.0440   1.0000   0.0919
 -13.250  -0.9255   0.06851   0.06213  -0.0484   1.0000   0.0911
 -13.000  -0.9639   0.06220   0.05560  -0.0503   1.0000   0.0906
 -12.750  -0.9951   0.05751   0.05067  -0.0498   1.0000   0.0903
 -12.500  -1.0204   0.05385   0.04676  -0.0476   1.0000   0.0903
 -12.250  -1.0416   0.05083   0.04349  -0.0441   1.0000   0.0904
 -12.000  -1.0581   0.04826   0.04066  -0.0399   1.0000   0.0908
 -11.750  -1.0689   0.04577   0.03785  -0.0362   1.0000   0.0915
 -11.500  -1.0754   0.04353   0.03524  -0.0325   1.0000   0.0924
 -11.250  -1.0616   0.04124   0.03295  -0.0312   1.0000   0.0942
 -11.000  -1.0479   0.03963   0.03130  -0.0297   1.0000   0.0961
 -10.750  -1.0372   0.03796   0.02949  -0.0276   1.0000   0.0980
 -10.500  -1.0265   0.03622   0.02757  -0.0254   1.0000   0.1000
 -10.250  -1.0157   0.03458   0.02567  -0.0231   1.0000   0.1023
 -10.000  -1.0003   0.03298   0.02396  -0.0214   1.0000   0.1051
  -9.750  -0.9824   0.03186   0.02294  -0.0200   1.0000   0.1085
  -9.500  -0.9670   0.03066   0.02164  -0.0181   1.0000   0.1124
  -9.250  -0.9512   0.02932   0.02013  -0.0162   1.0000   0.1164
  -9.000  -0.9339   0.02831   0.01925  -0.0146   1.0000   0.1213
  -8.750  -0.9193   0.02733   0.01810  -0.0123   1.0000   0.1282
  -8.500  -0.9036   0.02634   0.01729  -0.0104   1.0000   0.1357
  -8.250  -0.8892   0.02531   0.01626  -0.0081   1.0000   0.1460
  -8.000  -0.8766   0.02430   0.01533  -0.0055   1.0000   0.1611
  -7.750  -0.8665   0.02341   0.01456  -0.0025   1.0000   0.1832
  -7.500  -0.8563   0.02275   0.01399   0.0005   1.0000   0.2068
  -7.250  -0.8435   0.02237   0.01367   0.0032   1.0000   0.2258
  -7.000  -0.8290   0.02208   0.01336   0.0056   1.0000   0.2415
  -6.750  -0.8135   0.02179   0.01302   0.0079   1.0000   0.2552
  -6.500  -0.7976   0.02154   0.01267   0.0102   1.0000   0.2679
  -6.250  -0.7797   0.02126   0.01250   0.0120   1.0000   0.2787
  -6.000  -0.7626   0.02099   0.01220   0.0140   1.0000   0.2902
  -5.750  -0.7462   0.02076   0.01185   0.0162   1.0000   0.3026
  -5.500  -0.7277   0.02052   0.01173   0.0180   1.0000   0.3137
  -5.250  -0.7097   0.02023   0.01145   0.0198   1.0000   0.3253
  -5.000  -0.6922   0.01993   0.01107   0.0218   1.0000   0.3379
  -4.750  -0.6739   0.01969   0.01089   0.0236   1.0000   0.3509
  -4.500  -0.6556   0.01941   0.01069   0.0254   1.0000   0.3646
  -4.250  -0.6374   0.01909   0.01040   0.0271   1.0000   0.3792
  -4.000  -0.6191   0.01874   0.01007   0.0289   1.0000   0.3944
  -3.750  -0.6005   0.01839   0.00973   0.0305   1.0000   0.4103
  -3.500  -0.5821   0.01807   0.00944   0.0322   1.0000   0.4271
  -3.250  -0.5636   0.01776   0.00920   0.0338   1.0000   0.4442
  -3.000  -0.5454   0.01746   0.00901   0.0355   1.0000   0.4619
  -2.750  -0.5275   0.01720   0.00885   0.0371   1.0000   0.4797
  -2.500  -0.5099   0.01697   0.00873   0.0388   1.0000   0.4977
  -2.250  -0.4929   0.01679   0.00865   0.0404   1.0000   0.5163
  -2.000  -0.4764   0.01665   0.00864   0.0421   1.0000   0.5357
  -1.750  -0.4324   0.01668   0.00890   0.0386   0.9904   0.5633
  -1.500  -0.3807   0.01667   0.00912   0.0338   0.9764   0.5965
  -1.250  -0.3299   0.01653   0.00921   0.0294   0.9617   0.6342
  -1.000  -0.2788   0.01625   0.00920   0.0253   0.9466   0.6808
  -0.750  -0.2239   0.01592   0.00924   0.0210   0.9319   0.7373
  -0.500  -0.1603   0.01581   0.00948   0.0158   0.9185   0.8039
  -0.250  -0.0816   0.01584   0.00964   0.0082   0.9077   0.8597
   0.000  -0.0001   0.01586   0.00969   0.0000   0.8899   0.8900
   0.250   0.0817   0.01584   0.00964  -0.0082   0.8596   0.9077
   0.500   0.1600   0.01581   0.00948  -0.0158   0.8036   0.9184
   0.750   0.2238   0.01591   0.00924  -0.0210   0.7371   0.9319
   1.000   0.2788   0.01625   0.00920  -0.0253   0.6806   0.9466
   1.250   0.3299   0.01653   0.00921  -0.0294   0.6341   0.9618
   1.500   0.3809   0.01667   0.00912  -0.0338   0.5965   0.9765
   1.750   0.4324   0.01668   0.00890  -0.0386   0.5633   0.9904
   2.000   0.4763   0.01664   0.00864  -0.0421   0.5359   1.0000
   2.250   0.4928   0.01679   0.00865  -0.0404   0.5165   1.0000
   2.500   0.5099   0.01697   0.00872  -0.0388   0.4978   1.0000
   2.750   0.5274   0.01720   0.00885  -0.0371   0.4797   1.0000
   3.000   0.5453   0.01746   0.00901  -0.0355   0.4619   1.0000
   3.250   0.5636   0.01776   0.00920  -0.0338   0.4442   1.0000
   3.500   0.5820   0.01807   0.00943  -0.0322   0.4271   1.0000
   3.750   0.6005   0.01839   0.00973  -0.0305   0.4104   1.0000
   4.000   0.6190   0.01874   0.01007  -0.0288   0.3945   1.0000
   4.250   0.6374   0.01909   0.01040  -0.0271   0.3792   1.0000
   4.500   0.6555   0.01940   0.01068  -0.0253   0.3645   1.0000
   4.750   0.6738   0.01968   0.01088  -0.0235   0.3507   1.0000
   5.000   0.6922   0.01993   0.01107  -0.0218   0.3379   1.0000
   5.250   0.7097   0.02024   0.01146  -0.0198   0.3255   1.0000
   5.500   0.7277   0.02052   0.01173  -0.0180   0.3139   1.0000
   5.750   0.7462   0.02076   0.01186  -0.0162   0.3027   1.0000
   6.000   0.7626   0.02099   0.01220  -0.0140   0.2902   1.0000
   6.250   0.7796   0.02126   0.01250  -0.0120   0.2787   1.0000
   6.500   0.7977   0.02154   0.01267  -0.0102   0.2680   1.0000
   6.750   0.8135   0.02179   0.01302  -0.0079   0.2552   1.0000
   7.000   0.8290   0.02207   0.01335  -0.0056   0.2415   1.0000
   7.250   0.8435   0.02238   0.01367  -0.0032   0.2259   1.0000
   7.500   0.8563   0.02275   0.01399  -0.0005   0.2069   1.0000
   7.750   0.8665   0.02341   0.01456   0.0025   0.1833   1.0000
   8.000   0.8767   0.02430   0.01533   0.0055   0.1611   1.0000
   8.250   0.8894   0.02531   0.01626   0.0081   0.1462   1.0000
   8.500   0.9036   0.02635   0.01729   0.0104   0.1357   1.0000
   8.750   0.9195   0.02734   0.01810   0.0123   0.1283   1.0000
   9.000   0.9340   0.02831   0.01925   0.0146   0.1214   1.0000
   9.250   0.9513   0.02932   0.02013   0.0162   0.1165   1.0000
   9.500   0.9671   0.03066   0.02163   0.0181   0.1124   1.0000
   9.750   0.9825   0.03187   0.02295   0.0200   0.1086   1.0000
  10.000   1.0004   0.03298   0.02397   0.0214   0.1051   1.0000
  10.250   1.0158   0.03458   0.02567   0.0231   0.1023   1.0000
  10.500   1.0266   0.03622   0.02756   0.0254   0.1000   1.0000
  10.750   1.0374   0.03796   0.02950   0.0276   0.0980   1.0000
  11.000   1.0481   0.03963   0.03130   0.0297   0.0961   1.0000
  11.250   1.0620   0.04122   0.03293   0.0312   0.0942   1.0000
  11.500   1.0759   0.04356   0.03528   0.0324   0.0924   1.0000
  11.750   1.0687   0.04580   0.03789   0.0362   0.0915   1.0000
  12.000   1.0586   0.04829   0.04068   0.0399   0.0908   1.0000
  12.250   1.0417   0.05085   0.04351   0.0441   0.0904   1.0000
  12.500   1.0212   0.05384   0.04675   0.0475   0.0903   1.0000
  12.750   0.9950   0.05757   0.05073   0.0497   0.0903   1.0000
  13.000   0.9648   0.06221   0.05561   0.0502   0.0906   1.0000
  13.250   0.9267   0.06851   0.06213   0.0484   0.0911   1.0000
  13.500   0.8819   0.07711   0.07092   0.0438   0.0919   1.0000
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