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St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: St. CYR 171 (Royer) (stcyr171-il)
Reynolds number: 50,000
Max Cl/Cd: 23.13 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-stcyr171-il-50000-n5.txt
Download as CSV file: xf-stcyr171-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6576   0.10002   0.09182  -0.0137   1.0000   0.0815
 -11.250  -0.6757   0.09213   0.08399  -0.0176   1.0000   0.0827
 -10.750  -0.8505   0.05774   0.04926  -0.0378   1.0000   0.0776
 -10.500  -0.8546   0.05555   0.04705  -0.0362   1.0000   0.0791
 -10.250  -0.8605   0.05285   0.04425  -0.0347   1.0000   0.0808
 -10.000  -0.8649   0.04999   0.04121  -0.0332   1.0000   0.0831
  -9.750  -0.8673   0.04694   0.03787  -0.0315   1.0000   0.0859
  -9.500  -0.8668   0.04371   0.03421  -0.0296   1.0000   0.0892
  -9.250  -0.8547   0.04237   0.03294  -0.0279   1.0000   0.0923
  -9.000  -0.8437   0.04080   0.03128  -0.0261   1.0000   0.0967
  -8.750  -0.8345   0.03850   0.02859  -0.0241   1.0000   0.1035
  -8.500  -0.8209   0.03752   0.02773  -0.0222   1.0000   0.1097
  -8.250  -0.8085   0.03598   0.02596  -0.0203   1.0000   0.1204
  -8.000  -0.7941   0.03513   0.02506  -0.0186   1.0000   0.1317
  -7.750  -0.7790   0.03430   0.02417  -0.0168   1.0000   0.1427
  -7.500  -0.7633   0.03328   0.02285  -0.0152   1.0000   0.1544
  -7.250  -0.7464   0.03278   0.02236  -0.0135   1.0000   0.1650
  -7.000  -0.7292   0.03208   0.02155  -0.0119   1.0000   0.1754
  -6.750  -0.7117   0.03148   0.02076  -0.0104   1.0000   0.1870
  -6.500  -0.6938   0.03102   0.02033  -0.0088   1.0000   0.1974
  -6.250  -0.6756   0.03037   0.01949  -0.0073   1.0000   0.2087
  -6.000  -0.6568   0.02975   0.01881  -0.0058   1.0000   0.2181
  -5.750  -0.6376   0.02901   0.01795  -0.0044   1.0000   0.2268
  -5.500  -0.6181   0.02828   0.01717  -0.0029   1.0000   0.2347
  -5.250  -0.5976   0.02754   0.01624  -0.0016   1.0000   0.2417
  -5.000  -0.5777   0.02683   0.01555  -0.0001   1.0000   0.2477
  -4.750  -0.5570   0.02620   0.01481   0.0013   1.0000   0.2547
  -4.500  -0.5371   0.02558   0.01419   0.0028   1.0000   0.2618
  -4.250  -0.5173   0.02500   0.01358   0.0043   1.0000   0.2712
  -4.000  -0.4981   0.02446   0.01310   0.0059   1.0000   0.2806
  -3.750  -0.4785   0.02398   0.01264   0.0075   1.0000   0.2917
  -3.500  -0.4605   0.02364   0.01249   0.0094   1.0000   0.3021
  -3.250  -0.4427   0.02352   0.01260   0.0115   1.0000   0.3137
  -3.000  -0.4254   0.02373   0.01314   0.0137   1.0000   0.3267
  -2.750  -0.4076   0.02419   0.01391   0.0161   1.0000   0.3404
  -2.250  -0.3696   0.02672   0.01588   0.0196   1.0000   0.4281
  -2.000  -0.3533   0.02732   0.01629   0.0216   1.0000   0.4457
  -1.750  -0.3375   0.02734   0.01618   0.0235   1.0000   0.4604
  -1.500  -0.3223   0.02707   0.01577   0.0254   1.0000   0.4748
  -1.250  -0.3072   0.02663   0.01520   0.0271   1.0000   0.4884
  -1.000  -0.2738   0.02590   0.01433   0.0251   0.9901   0.5051
  -0.750  -0.2371   0.02505   0.01336   0.0225   0.9783   0.5208
  -0.500  -0.1991   0.02414   0.01237   0.0198   0.9666   0.5349
  -0.250  -0.1626   0.02342   0.01160   0.0175   0.9536   0.5467
   0.000  -0.1231   0.02259   0.01080   0.0148   0.9412   0.5579
   0.250  -0.0770   0.02201   0.01031   0.0110   0.9292   0.5673
   0.500  -0.0237   0.02145   0.00987   0.0063   0.9100   0.5749
   0.750   0.0372   0.02077   0.00935   0.0011   0.8810   0.5804
   1.000   0.0882   0.02022   0.00892  -0.0020   0.8465   0.5839
   1.250   0.1328   0.01986   0.00867  -0.0041   0.8163   0.5869
   1.500   0.1706   0.01961   0.00852  -0.0050   0.7850   0.5903
   1.750   0.2057   0.01941   0.00842  -0.0054   0.7512   0.5936
   2.000   0.2366   0.01927   0.00838  -0.0050   0.7145   0.5974
   2.250   0.2630   0.01923   0.00841  -0.0038   0.6722   0.6010
   2.500   0.2867   0.01926   0.00850  -0.0022   0.6233   0.6039
   2.750   0.3097   0.01939   0.00852  -0.0003   0.5643   0.6060
   3.000   0.3316   0.01972   0.00859   0.0015   0.5001   0.6071
   3.250   0.3527   0.02021   0.00882   0.0032   0.4326   0.6069
   3.500   0.3745   0.02086   0.00907   0.0045   0.3773   0.6053
   3.750   0.3974   0.02160   0.00944   0.0054   0.3421   0.6034
   4.000   0.4219   0.02233   0.00996   0.0060   0.3181   0.6016
   4.250   0.4474   0.02307   0.01056   0.0064   0.3011   0.6000
   4.500   0.4736   0.02383   0.01119   0.0067   0.2870   0.5985
   4.750   0.5003   0.02453   0.01191   0.0070   0.2736   0.5971
   5.000   0.5269   0.02529   0.01265   0.0073   0.2631   0.5958
   5.250   0.5540   0.02606   0.01346   0.0075   0.2542   0.5947
   5.500   0.5811   0.02692   0.01427   0.0077   0.2468   0.5935
   5.750   0.6068   0.02772   0.01527   0.0082   0.2381   0.5925
   6.000   0.6327   0.02860   0.01612   0.0085   0.2304   0.5915
   6.250   0.6580   0.02957   0.01728   0.0090   0.2236   0.5905
   6.500   0.6820   0.03048   0.01836   0.0097   0.2155   0.5896
   6.750   0.7041   0.03133   0.01930   0.0105   0.2051   0.5888
   7.000   0.7244   0.03191   0.01987   0.0116   0.1923   0.5879
   7.250   0.7420   0.03250   0.02068   0.0130   0.1782   0.5870
   7.500   0.7598   0.03308   0.02137   0.0144   0.1652   0.5862
   7.750   0.7791   0.03369   0.02196   0.0155   0.1549   0.5854
   8.000   0.7968   0.03482   0.02348   0.0169   0.1437   0.5846
   8.250   0.8144   0.03581   0.02455   0.0182   0.1339   0.5838
   8.500   0.8302   0.03688   0.02579   0.0198   0.1229   0.5830
   8.750   0.8444   0.03837   0.02751   0.0213   0.1126   0.5823
   9.000   0.8596   0.03920   0.02828   0.0228   0.1054   0.5816
   9.250   0.8710   0.04145   0.03094   0.0244   0.0984   0.5809
   9.500   0.8832   0.04315   0.03280   0.0260   0.0938   0.5802
   9.750   0.8973   0.04444   0.03405   0.0274   0.0906   0.5795
  10.000   0.8996   0.04759   0.03764   0.0293   0.0876   0.5789
  10.250   0.8972   0.05074   0.04115   0.0313   0.0851   0.5783
  10.500   0.8920   0.05368   0.04436   0.0332   0.0829   0.5777
  10.750   0.8829   0.05646   0.04733   0.0354   0.0814   0.5771
  11.000   0.8783   0.05874   0.04970   0.0370   0.0795   0.5764
  11.250   0.8753   0.06112   0.05213   0.0380   0.0781   0.5758
  11.500   0.8650   0.06451   0.05558   0.0382   0.0771   0.5753
  11.750   0.8323   0.07111   0.06238   0.0357   0.0772   0.5748
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