Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

St. CYR 172 (Royer) (stcyr172-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: St. CYR 172 (Royer) (stcyr172-il)
Reynolds number: 100,000
Max Cl/Cd: 38.81 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-stcyr172-il-100000-n5.txt
Download as CSV file: xf-stcyr172-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.9164   0.09012   0.08333  -0.0344   1.0000   0.0547
 -15.250  -0.9503   0.08104   0.07400  -0.0401   1.0000   0.0546
 -15.000  -0.9730   0.07431   0.06704  -0.0439   1.0000   0.0549
 -14.750  -0.9900   0.06879   0.06130  -0.0468   1.0000   0.0552
 -14.500  -1.0039   0.06400   0.05629  -0.0489   1.0000   0.0557
 -14.250  -1.0145   0.05989   0.05197  -0.0504   1.0000   0.0562
 -14.000  -1.0219   0.05635   0.04822  -0.0512   1.0000   0.0567
 -13.750  -1.0279   0.05318   0.04482  -0.0515   1.0000   0.0572
 -13.500  -1.0265   0.05067   0.04218  -0.0512   1.0000   0.0578
 -13.250  -1.0176   0.04876   0.04027  -0.0505   1.0000   0.0585
 -13.000  -1.0118   0.04683   0.03833  -0.0499   1.0000   0.0595
 -12.750  -1.0074   0.04491   0.03634  -0.0491   1.0000   0.0604
 -12.500  -1.0035   0.04303   0.03438  -0.0481   1.0000   0.0614
 -12.250  -0.9997   0.04124   0.03249  -0.0470   1.0000   0.0626
 -12.000  -0.9950   0.03957   0.03072  -0.0456   1.0000   0.0637
 -11.750  -0.9896   0.03803   0.02904  -0.0439   1.0000   0.0648
 -11.500  -0.9833   0.03661   0.02750  -0.0422   1.0000   0.0658
 -11.250  -0.9781   0.03520   0.02607  -0.0401   1.0000   0.0668
 -11.000  -0.9741   0.03389   0.02475  -0.0377   1.0000   0.0679
 -10.750  -0.9704   0.03271   0.02354  -0.0349   1.0000   0.0692
 -10.500  -0.9665   0.03164   0.02243  -0.0320   1.0000   0.0708
 -10.250  -0.9623   0.03064   0.02137  -0.0288   1.0000   0.0727
 -10.000  -0.9555   0.02967   0.02030  -0.0258   1.0000   0.0747
  -9.750  -0.9490   0.02865   0.01928  -0.0229   1.0000   0.0767
  -9.500  -0.9415   0.02768   0.01831  -0.0201   1.0000   0.0792
  -9.250  -0.9317   0.02679   0.01738  -0.0174   1.0000   0.0822
  -9.000  -0.9210   0.02593   0.01649  -0.0148   1.0000   0.0859
  -8.750  -0.9105   0.02505   0.01565  -0.0122   1.0000   0.0912
  -8.500  -0.8987   0.02424   0.01488  -0.0098   1.0000   0.0990
  -8.250  -0.8860   0.02348   0.01419  -0.0074   1.0000   0.1110
  -8.000  -0.8720   0.02281   0.01357  -0.0052   1.0000   0.1268
  -7.750  -0.8567   0.02224   0.01300  -0.0031   1.0000   0.1432
  -7.500  -0.8410   0.02173   0.01246  -0.0010   1.0000   0.1576
  -7.250  -0.8249   0.02126   0.01198   0.0010   1.0000   0.1706
  -7.000  -0.8081   0.02083   0.01153   0.0029   1.0000   0.1825
  -6.750  -0.7912   0.02043   0.01110   0.0048   1.0000   0.1934
  -6.500  -0.7746   0.02004   0.01073   0.0068   1.0000   0.2041
  -6.250  -0.7574   0.01969   0.01038   0.0087   1.0000   0.2156
  -6.000  -0.7398   0.01937   0.01004   0.0105   1.0000   0.2273
  -5.750  -0.7229   0.01904   0.00976   0.0125   1.0000   0.2382
  -5.500  -0.7054   0.01875   0.00948   0.0143   1.0000   0.2493
  -5.250  -0.6872   0.01849   0.00920   0.0161   1.0000   0.2609
  -5.000  -0.6698   0.01822   0.00899   0.0180   1.0000   0.2725
  -4.750  -0.6521   0.01799   0.00880   0.0198   1.0000   0.2860
  -4.500  -0.6342   0.01779   0.00863   0.0216   1.0000   0.3001
  -4.250  -0.6160   0.01761   0.00847   0.0233   1.0000   0.3143
  -4.000  -0.5833   0.01743   0.00831   0.0221   0.9951   0.3305
  -3.750  -0.5414   0.01723   0.00812   0.0191   0.9856   0.3472
  -3.500  -0.5035   0.01701   0.00791   0.0170   0.9766   0.3629
  -3.250  -0.4661   0.01679   0.00773   0.0151   0.9681   0.3786
  -3.000  -0.4300   0.01654   0.00753   0.0134   0.9585   0.3942
  -2.750  -0.3948   0.01627   0.00732   0.0121   0.9479   0.4093
  -2.500  -0.3577   0.01600   0.00712   0.0103   0.9381   0.4247
  -2.250  -0.3182   0.01571   0.00689   0.0082   0.9285   0.4415
  -2.000  -0.2817   0.01541   0.00669   0.0068   0.9167   0.4593
  -1.750  -0.2432   0.01512   0.00651   0.0050   0.9048   0.4789
  -1.500  -0.2053   0.01482   0.00634   0.0033   0.8913   0.5006
  -1.250  -0.1708   0.01454   0.00619   0.0024   0.8744   0.5261
  -1.000  -0.1396   0.01426   0.00610   0.0023   0.8535   0.5580
  -0.750  -0.1080   0.01398   0.00601   0.0022   0.8296   0.5991
  -0.500  -0.0780   0.01372   0.00595   0.0025   0.7995   0.6434
  -0.250  -0.0409   0.01351   0.00583   0.0016   0.7653   0.6871
   0.000   0.0000   0.01341   0.00576   0.0000   0.7276   0.7277
   0.250   0.0409   0.01351   0.00583  -0.0015   0.6871   0.7652
   0.500   0.0779   0.01372   0.00595  -0.0025   0.6430   0.7994
   0.750   0.1080   0.01398   0.00601  -0.0022   0.5989   0.8296
   1.000   0.1396   0.01426   0.00610  -0.0023   0.5578   0.8535
   1.250   0.1707   0.01454   0.00619  -0.0024   0.5259   0.8744
   1.500   0.2054   0.01482   0.00634  -0.0034   0.5008   0.8913
   1.750   0.2433   0.01512   0.00651  -0.0050   0.4789   0.9049
   2.000   0.2818   0.01541   0.00669  -0.0068   0.4595   0.9167
   2.250   0.3181   0.01571   0.00689  -0.0082   0.4417   0.9285
   2.500   0.3576   0.01600   0.00711  -0.0103   0.4249   0.9380
   2.750   0.3949   0.01627   0.00732  -0.0121   0.4094   0.9479
   3.000   0.4301   0.01654   0.00753  -0.0134   0.3941   0.9585
   3.250   0.4661   0.01679   0.00773  -0.0151   0.3786   0.9682
   3.500   0.5036   0.01701   0.00791  -0.0171   0.3629   0.9767
   3.750   0.5415   0.01723   0.00812  -0.0191   0.3472   0.9856
   4.000   0.5834   0.01743   0.00831  -0.0221   0.3305   0.9951
   4.250   0.6160   0.01761   0.00847  -0.0233   0.3144   1.0000
   4.500   0.6342   0.01779   0.00863  -0.0216   0.3002   1.0000
   4.750   0.6521   0.01799   0.00879  -0.0198   0.2860   1.0000
   5.000   0.6697   0.01822   0.00899  -0.0180   0.2725   1.0000
   5.250   0.6871   0.01848   0.00919  -0.0161   0.2608   1.0000
   5.500   0.7053   0.01875   0.00948  -0.0143   0.2493   1.0000
   5.750   0.7229   0.01904   0.00976  -0.0125   0.2382   1.0000
   6.000   0.7398   0.01937   0.01004  -0.0105   0.2272   1.0000
   6.250   0.7574   0.01969   0.01038  -0.0087   0.2157   1.0000
   6.500   0.7745   0.02004   0.01073  -0.0068   0.2039   1.0000
   6.750   0.7911   0.02043   0.01110  -0.0048   0.1933   1.0000
   7.000   0.8080   0.02083   0.01152  -0.0029   0.1823   1.0000
   7.250   0.8248   0.02125   0.01198  -0.0010   0.1703   1.0000
   7.500   0.8409   0.02173   0.01246   0.0010   0.1576   1.0000
   7.750   0.8567   0.02224   0.01300   0.0031   0.1433   1.0000
   8.000   0.8720   0.02281   0.01357   0.0052   0.1268   1.0000
   8.250   0.8859   0.02349   0.01419   0.0074   0.1105   1.0000
   8.500   0.8986   0.02425   0.01488   0.0098   0.0986   1.0000
   8.750   0.9105   0.02506   0.01565   0.0122   0.0909   1.0000
   9.000   0.9210   0.02593   0.01649   0.0148   0.0858   1.0000
   9.250   0.9318   0.02679   0.01738   0.0174   0.0823   1.0000
   9.500   0.9415   0.02768   0.01831   0.0201   0.0792   1.0000
   9.750   0.9492   0.02865   0.01928   0.0229   0.0767   1.0000
  10.000   0.9556   0.02968   0.02030   0.0258   0.0747   1.0000
  10.250   0.9624   0.03065   0.02137   0.0287   0.0725   1.0000
  10.500   0.9668   0.03164   0.02243   0.0319   0.0708   1.0000
  10.750   0.9708   0.03271   0.02354   0.0349   0.0693   1.0000
  11.000   0.9744   0.03390   0.02476   0.0376   0.0679   1.0000
  11.250   0.9785   0.03521   0.02607   0.0400   0.0668   1.0000
  11.500   0.9840   0.03660   0.02747   0.0421   0.0658   1.0000
  11.750   0.9901   0.03803   0.02904   0.0439   0.0648   1.0000
  12.000   0.9957   0.03957   0.03071   0.0455   0.0637   1.0000
  12.250   1.0001   0.04124   0.03250   0.0469   0.0625   1.0000
  12.500   1.0046   0.04301   0.03436   0.0481   0.0615   1.0000
  12.750   1.0082   0.04489   0.03632   0.0490   0.0604   1.0000
  13.000   1.0128   0.04681   0.03830   0.0498   0.0594   1.0000
  13.250   1.0188   0.04875   0.04026   0.0505   0.0586   1.0000
  13.500   1.0277   0.05064   0.04216   0.0511   0.0578   1.0000
  13.750   1.0289   0.05317   0.04481   0.0514   0.0572   1.0000
  14.000   1.0235   0.05630   0.04816   0.0511   0.0567   1.0000
  14.250   1.0154   0.05991   0.05200   0.0502   0.0562   1.0000
  14.500   1.0047   0.06403   0.05633   0.0487   0.0557   1.0000
  14.750   0.9919   0.06872   0.06123   0.0467   0.0553   1.0000
  15.000   0.9746   0.07428   0.06701   0.0438   0.0549   1.0000
  15.250   0.9517   0.08106   0.07402   0.0399   0.0547   1.0000
  15.500   0.9175   0.09017   0.08339   0.0342   0.0546   1.0000
<< Back to St. CYR 172 (Royer) (stcyr172-il)

Polar data table (+)

Polar graphs


<< Back to St. CYR 172 (Royer) (stcyr172-il)