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St. CYR 172 (Royer) (stcyr172-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: St. CYR 172 (Royer) (stcyr172-il)
Reynolds number: 50,000
Max Cl/Cd: 26.99 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-stcyr172-il-50000-n5.txt
Download as CSV file: xf-stcyr172-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7365   0.09455   0.08586  -0.0269   1.0000   0.0942
 -12.750  -0.8193   0.07581   0.06688  -0.0385   1.0000   0.0936
 -12.500  -0.8578   0.06703   0.05784  -0.0431   1.0000   0.0938
 -12.250  -0.8835   0.06105   0.05161  -0.0452   1.0000   0.0945
 -12.000  -0.9010   0.05656   0.04685  -0.0457   1.0000   0.0955
 -11.750  -0.9037   0.05377   0.04397  -0.0450   1.0000   0.0969
 -11.500  -0.9009   0.05168   0.04186  -0.0440   1.0000   0.0986
 -11.250  -0.9016   0.04952   0.03962  -0.0427   1.0000   0.1008
 -11.000  -0.9037   0.04732   0.03729  -0.0409   1.0000   0.1034
 -10.750  -0.9059   0.04512   0.03486  -0.0388   1.0000   0.1064
 -10.500  -0.9036   0.04349   0.03320  -0.0365   1.0000   0.1095
 -10.250  -0.9003   0.04211   0.03183  -0.0339   1.0000   0.1130
 -10.000  -0.8966   0.04049   0.03008  -0.0314   1.0000   0.1176
  -9.750  -0.8901   0.03899   0.02851  -0.0290   1.0000   0.1225
  -9.500  -0.8836   0.03771   0.02723  -0.0266   1.0000   0.1289
  -9.250  -0.8764   0.03634   0.02578  -0.0241   1.0000   0.1369
  -9.000  -0.8691   0.03507   0.02443  -0.0215   1.0000   0.1473
  -8.750  -0.8608   0.03396   0.02339  -0.0189   1.0000   0.1580
  -8.500  -0.8519   0.03291   0.02234  -0.0164   1.0000   0.1707
  -8.250  -0.8422   0.03199   0.02139  -0.0138   1.0000   0.1845
  -8.000  -0.8312   0.03117   0.02051  -0.0113   1.0000   0.1984
  -7.750  -0.8191   0.03044   0.01969  -0.0090   1.0000   0.2122
  -7.500  -0.8058   0.02987   0.01913  -0.0067   1.0000   0.2250
  -7.250  -0.7916   0.02934   0.01861  -0.0044   1.0000   0.2373
  -7.000  -0.7776   0.02887   0.01810  -0.0022   1.0000   0.2508
  -6.750  -0.7638   0.02846   0.01769   0.0001   1.0000   0.2654
  -6.500  -0.7498   0.02811   0.01731   0.0025   1.0000   0.2804
  -6.250  -0.7352   0.02770   0.01683   0.0047   1.0000   0.2947
  -6.000  -0.7185   0.02733   0.01648   0.0067   1.0000   0.3073
  -5.750  -0.7010   0.02688   0.01604   0.0086   1.0000   0.3189
  -5.500  -0.6834   0.02632   0.01538   0.0104   1.0000   0.3305
  -5.250  -0.6642   0.02580   0.01485   0.0119   1.0000   0.3407
  -5.000  -0.6448   0.02525   0.01426   0.0134   1.0000   0.3511
  -4.750  -0.6264   0.02474   0.01364   0.0151   1.0000   0.3638
  -4.500  -0.6067   0.02429   0.01325   0.0166   1.0000   0.3755
  -4.250  -0.5873   0.02385   0.01279   0.0181   1.0000   0.3883
  -4.000  -0.5681   0.02342   0.01233   0.0196   1.0000   0.4022
  -3.750  -0.5486   0.02303   0.01195   0.0210   1.0000   0.4165
  -3.500  -0.5286   0.02266   0.01164   0.0224   1.0000   0.4310
  -3.250  -0.5087   0.02233   0.01135   0.0237   1.0000   0.4464
  -3.000  -0.4889   0.02203   0.01111   0.0251   1.0000   0.4628
  -2.750  -0.4691   0.02176   0.01091   0.0264   1.0000   0.4798
  -2.500  -0.4498   0.02152   0.01076   0.0278   1.0000   0.4980
  -2.250  -0.4317   0.02133   0.01068   0.0293   1.0000   0.5172
  -1.750  -0.3588   0.02105   0.01075   0.0255   0.9804   0.5739
  -1.500  -0.3165   0.02087   0.01080   0.0228   0.9645   0.6104
  -1.250  -0.2738   0.02069   0.01083   0.0202   0.9480   0.6522
  -1.000  -0.2271   0.02053   0.01094   0.0173   0.9319   0.6956
  -0.750  -0.1742   0.02046   0.01112   0.0136   0.9159   0.7403
  -0.500  -0.1134   0.02051   0.01134   0.0087   0.8996   0.7826
  -0.250  -0.0517   0.02056   0.01146   0.0035   0.8804   0.8211
   0.000   0.0000   0.02058   0.01149   0.0000   0.8535   0.8536
   0.250   0.0518   0.02056   0.01146  -0.0035   0.8211   0.8805
   0.500   0.1134   0.02051   0.01134  -0.0087   0.7827   0.8997
   0.750   0.1742   0.02046   0.01112  -0.0136   0.7404   0.9159
   1.000   0.2270   0.02053   0.01094  -0.0173   0.6957   0.9318
   1.250   0.2737   0.02069   0.01083  -0.0202   0.6521   0.9480
   1.500   0.3164   0.02087   0.01080  -0.0228   0.6103   0.9645
   1.750   0.3589   0.02105   0.01075  -0.0255   0.5737   0.9804
   2.000   0.4035   0.02118   0.01066  -0.0289   0.5416   0.9949
   2.250   0.4316   0.02132   0.01068  -0.0293   0.5173   1.0000
   2.500   0.4497   0.02152   0.01076  -0.0278   0.4982   1.0000
   2.750   0.4691   0.02176   0.01091  -0.0264   0.4799   1.0000
   3.000   0.4887   0.02202   0.01110  -0.0250   0.4626   1.0000
   3.250   0.5087   0.02233   0.01135  -0.0238   0.4466   1.0000
   3.500   0.5285   0.02266   0.01163  -0.0224   0.4310   1.0000
   3.750   0.5485   0.02303   0.01194  -0.0210   0.4165   1.0000
   4.000   0.5681   0.02342   0.01233  -0.0196   0.4022   1.0000
   4.250   0.5873   0.02384   0.01279  -0.0181   0.3883   1.0000
   4.500   0.6066   0.02429   0.01325  -0.0166   0.3754   1.0000
   4.750   0.6264   0.02474   0.01364  -0.0151   0.3638   1.0000
   5.000   0.6448   0.02525   0.01426  -0.0134   0.3512   1.0000
   5.250   0.6641   0.02580   0.01484  -0.0119   0.3408   1.0000
   5.500   0.6834   0.02632   0.01538  -0.0104   0.3305   1.0000
   5.750   0.7010   0.02688   0.01604  -0.0086   0.3189   1.0000
   6.000   0.7185   0.02733   0.01648  -0.0067   0.3074   1.0000
   6.250   0.7352   0.02770   0.01683  -0.0047   0.2948   1.0000
   6.500   0.7497   0.02810   0.01729  -0.0025   0.2803   1.0000
   6.750   0.7637   0.02846   0.01768  -0.0001   0.2653   1.0000
   7.000   0.7775   0.02886   0.01811   0.0022   0.2507   1.0000
   7.250   0.7915   0.02933   0.01860   0.0045   0.2372   1.0000
   7.500   0.8058   0.02987   0.01913   0.0067   0.2249   1.0000
   7.750   0.8191   0.03044   0.01970   0.0089   0.2123   1.0000
   8.000   0.8312   0.03117   0.02051   0.0113   0.1984   1.0000
   8.250   0.8421   0.03198   0.02138   0.0138   0.1844   1.0000
   8.500   0.8518   0.03291   0.02233   0.0164   0.1704   1.0000
   8.750   0.8607   0.03397   0.02339   0.0189   0.1577   1.0000
   9.000   0.8690   0.03507   0.02444   0.0215   0.1471   1.0000
   9.250   0.8766   0.03633   0.02577   0.0241   0.1369   1.0000
   9.500   0.8836   0.03770   0.02722   0.0265   0.1287   1.0000
   9.750   0.8904   0.03898   0.02850   0.0290   0.1225   1.0000
  10.000   0.8968   0.04050   0.03009   0.0313   0.1175   1.0000
  10.250   0.9005   0.04211   0.03182   0.0339   0.1129   1.0000
  10.500   0.9039   0.04347   0.03318   0.0364   0.1094   1.0000
  10.750   0.9064   0.04513   0.03489   0.0387   0.1064   1.0000
  11.000   0.9041   0.04732   0.03729   0.0409   0.1033   1.0000
  11.250   0.9021   0.04951   0.03961   0.0426   0.1007   1.0000
  11.500   0.9017   0.05168   0.04186   0.0439   0.0986   1.0000
  11.750   0.9046   0.05376   0.04395   0.0449   0.0969   1.0000
  12.000   0.9014   0.05660   0.04689   0.0456   0.0954   1.0000
  12.250   0.8838   0.06110   0.05166   0.0451   0.0944   1.0000
  12.500   0.8590   0.06699   0.05780   0.0430   0.0938   1.0000
  12.750   0.8199   0.07588   0.06696   0.0383   0.0936   1.0000
  13.000   0.7356   0.09495   0.08626   0.0265   0.0942   1.0000
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