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=50,000 Ncrit=9


Details Polar file
Airfoil: St. CYR 172 (Royer) (stcyr172-il)
Reynolds number: 50,000
Max Cl/Cd: 22.82 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stcyr172-il-50000.txt
Download as CSV file: xf-stcyr172-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5669   0.10705   0.09859  -0.0092   1.0000   0.2141
 -10.500  -0.7007   0.08028   0.07208  -0.0284   1.0000   0.1867
 -10.250  -0.7473   0.07085   0.06267  -0.0321   1.0000   0.1846
 -10.000  -0.8015   0.06363   0.05541  -0.0311   1.0000   0.1818
  -9.750  -0.8445   0.05809   0.04969  -0.0279   1.0000   0.1812
  -9.500  -0.8717   0.05356   0.04489  -0.0244   1.0000   0.1828
  -9.250  -0.8934   0.04942   0.04035  -0.0205   1.0000   0.1856
  -9.000  -0.8841   0.04725   0.03817  -0.0184   1.0000   0.1922
  -8.750  -0.8822   0.04475   0.03547  -0.0155   1.0000   0.1998
  -8.500  -0.8738   0.04264   0.03329  -0.0130   1.0000   0.2090
  -8.250  -0.8721   0.04031   0.03071  -0.0096   1.0000   0.2209
  -8.000  -0.8591   0.03902   0.02948  -0.0071   1.0000   0.2376
  -7.750  -0.8409   0.03848   0.02916  -0.0047   1.0000   0.2590
  -7.500  -0.8296   0.03772   0.02838  -0.0016   1.0000   0.2819
  -7.250  -0.8206   0.03682   0.02735   0.0016   1.0000   0.3024
  -7.000  -0.8005   0.03668   0.02734   0.0038   1.0000   0.3216
  -6.750  -0.7859   0.03604   0.02664   0.0063   1.0000   0.3383
  -6.500  -0.7711   0.03550   0.02607   0.0089   1.0000   0.3552
  -6.250  -0.7517   0.03548   0.02617   0.0112   1.0000   0.3746
  -6.000  -0.7337   0.03524   0.02602   0.0136   1.0000   0.3935
  -5.750  -0.7228   0.03422   0.02488   0.0163   1.0000   0.4089
  -5.500  -0.7025   0.03341   0.02412   0.0181   1.0000   0.4217
  -5.250  -0.6878   0.03215   0.02278   0.0201   1.0000   0.4328
  -5.000  -0.6776   0.03073   0.02114   0.0225   1.0000   0.4451
  -4.750  -0.6572   0.02977   0.02025   0.0241   1.0000   0.4565
  -4.500  -0.6412   0.02868   0.01909   0.0260   1.0000   0.4696
  -4.250  -0.6254   0.02767   0.01803   0.0280   1.0000   0.4847
  -4.000  -0.6090   0.02676   0.01708   0.0299   1.0000   0.5011
  -3.750  -0.5916   0.02593   0.01626   0.0318   1.0000   0.5185
  -3.500  -0.5732   0.02523   0.01561   0.0337   1.0000   0.5374
  -3.250  -0.5546   0.02463   0.01511   0.0356   1.0000   0.5577
  -3.000  -0.5362   0.02410   0.01466   0.0376   1.0000   0.5793
  -2.750  -0.5187   0.02359   0.01420   0.0396   1.0000   0.6025
  -2.500  -0.5012   0.02313   0.01382   0.0416   1.0000   0.6271
  -2.250  -0.4816   0.02280   0.01362   0.0434   1.0000   0.6527
  -2.000  -0.4639   0.02244   0.01335   0.0453   1.0000   0.6813
  -1.750  -0.4432   0.02224   0.01331   0.0470   1.0000   0.7119
  -1.500  -0.4228   0.02217   0.01343   0.0490   1.0000   0.7451
  -1.250  -0.4007   0.02229   0.01373   0.0507   1.0000   0.7833
  -1.000  -0.3702   0.02271   0.01432   0.0511   1.0000   0.8278
  -0.750  -0.3132   0.02356   0.01526   0.0468   1.0000   0.8796
  -0.500  -0.2007   0.02498   0.01663   0.0322   1.0000   0.9259
  -0.250  -0.0759   0.02580   0.01740   0.0136   1.0000   0.9697
   0.000  -0.0001   0.02570   0.01728   0.0000   1.0000   1.0000
   0.250   0.0765   0.02580   0.01740  -0.0137   0.9695   1.0000
   0.500   0.2015   0.02496   0.01661  -0.0323   0.9257   1.0000
   0.750   0.3132   0.02356   0.01526  -0.0468   0.8797   1.0000
   1.000   0.3704   0.02270   0.01431  -0.0511   0.8276   1.0000
   1.250   0.4006   0.02229   0.01374  -0.0507   0.7831   1.0000
   1.500   0.4228   0.02216   0.01342  -0.0490   0.7452   1.0000
   1.750   0.4431   0.02224   0.01331  -0.0471   0.7120   1.0000
   2.000   0.4638   0.02244   0.01335  -0.0453   0.6815   1.0000
   2.250   0.4816   0.02280   0.01362  -0.0434   0.6529   1.0000
   2.500   0.5012   0.02314   0.01383  -0.0416   0.6273   1.0000
   2.750   0.5187   0.02359   0.01420  -0.0396   0.6026   1.0000
   3.000   0.5362   0.02409   0.01466  -0.0376   0.5793   1.0000
   3.250   0.5546   0.02463   0.01511  -0.0356   0.5577   1.0000
   3.500   0.5732   0.02523   0.01561  -0.0337   0.5374   1.0000
   3.750   0.5916   0.02593   0.01626  -0.0318   0.5186   1.0000
   4.000   0.6089   0.02676   0.01709  -0.0299   0.5012   1.0000
   4.250   0.6254   0.02767   0.01803  -0.0280   0.4847   1.0000
   4.500   0.6412   0.02868   0.01909  -0.0260   0.4696   1.0000
   4.750   0.6572   0.02977   0.02024  -0.0240   0.4564   1.0000
   5.000   0.6775   0.03072   0.02114  -0.0225   0.4451   1.0000
   5.250   0.6877   0.03215   0.02279  -0.0201   0.4329   1.0000
   5.500   0.7025   0.03341   0.02412  -0.0181   0.4217   1.0000
   5.750   0.7226   0.03423   0.02489  -0.0163   0.4090   1.0000
   6.000   0.7338   0.03523   0.02600  -0.0136   0.3935   1.0000
   6.250   0.7516   0.03548   0.02617  -0.0112   0.3746   1.0000
   6.500   0.7708   0.03553   0.02611  -0.0088   0.3554   1.0000
   6.750   0.7858   0.03605   0.02666  -0.0063   0.3384   1.0000
   7.000   0.8005   0.03667   0.02733  -0.0038   0.3215   1.0000
   7.250   0.8203   0.03684   0.02738  -0.0016   0.3025   1.0000
   7.500   0.8297   0.03771   0.02837   0.0016   0.2820   1.0000
   7.750   0.8408   0.03849   0.02916   0.0047   0.2590   1.0000
   8.000   0.8592   0.03900   0.02946   0.0071   0.2376   1.0000
   8.250   0.8713   0.04037   0.03080   0.0097   0.2211   1.0000
   8.500   0.8738   0.04264   0.03328   0.0130   0.2090   1.0000
   8.750   0.8824   0.04474   0.03546   0.0155   0.1998   1.0000
   9.000   0.8840   0.04727   0.03819   0.0184   0.1923   1.0000
   9.250   0.8937   0.04942   0.04034   0.0205   0.1857   1.0000
   9.500   0.8720   0.05354   0.04487   0.0244   0.1828   1.0000
   9.750   0.8447   0.05810   0.04971   0.0279   0.1812   1.0000
  10.000   0.8019   0.06368   0.05546   0.0311   0.1820   1.0000
  10.250   0.7476   0.07087   0.06269   0.0320   0.1846   1.0000
  10.500   0.7010   0.08031   0.07211   0.0283   0.1867   1.0000
  10.750   0.6053   0.10147   0.09309   0.0142   0.2021   1.0000
<< Back to St. CYR 172 (Royer) (stcyr172-il)

Polar data table (+)

Polar graphs


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