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St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: St. CYR 171 (Royer) (stcyr171-il)
Reynolds number: 100,000
Max Cl/Cd: 33.35 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stcyr171-il-100000.txt
Download as CSV file: xf-stcyr171-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7148   0.08122   0.07559  -0.0298   1.0000   0.0843
 -11.000  -0.7569   0.07052   0.06490  -0.0366   1.0000   0.0828
 -10.750  -0.8131   0.06089   0.05517  -0.0423   1.0000   0.0810
 -10.500  -0.8583   0.05484   0.04889  -0.0410   1.0000   0.0800
 -10.250  -0.8859   0.04947   0.04315  -0.0390   1.0000   0.0795
 -10.000  -0.8981   0.04529   0.03858  -0.0365   1.0000   0.0798
  -9.750  -0.9013   0.04182   0.03473  -0.0339   1.0000   0.0805
  -9.500  -0.8983   0.03890   0.03143  -0.0314   1.0000   0.0819
  -9.250  -0.8916   0.03639   0.02850  -0.0290   1.0000   0.0838
  -9.000  -0.8803   0.03414   0.02598  -0.0269   1.0000   0.0860
  -8.750  -0.8631   0.03282   0.02472  -0.0253   1.0000   0.0886
  -8.500  -0.8469   0.03137   0.02316  -0.0235   1.0000   0.0916
  -8.250  -0.8309   0.02973   0.02127  -0.0215   1.0000   0.0954
  -8.000  -0.8143   0.02819   0.01963  -0.0196   1.0000   0.0995
  -7.750  -0.7961   0.02739   0.01889  -0.0180   1.0000   0.1058
  -7.500  -0.7790   0.02628   0.01771  -0.0160   1.0000   0.1147
  -7.250  -0.7618   0.02535   0.01676  -0.0140   1.0000   0.1284
  -7.000  -0.7449   0.02472   0.01622  -0.0120   1.0000   0.1474
  -6.750  -0.7269   0.02435   0.01583  -0.0102   1.0000   0.1652
  -6.500  -0.7079   0.02403   0.01540  -0.0086   1.0000   0.1789
  -6.250  -0.6883   0.02387   0.01509  -0.0070   1.0000   0.1908
  -6.000  -0.6686   0.02361   0.01491  -0.0056   1.0000   0.2006
  -5.750  -0.6486   0.02322   0.01432  -0.0041   1.0000   0.2103
  -5.500  -0.6281   0.02276   0.01392  -0.0027   1.0000   0.2180
  -5.250  -0.6076   0.02241   0.01333  -0.0012   1.0000   0.2267
  -5.000  -0.5872   0.02171   0.01276   0.0001   1.0000   0.2340
  -4.750  -0.5665   0.02129   0.01219   0.0015   1.0000   0.2427
  -4.500  -0.5464   0.02064   0.01165   0.0029   1.0000   0.2515
  -4.250  -0.5262   0.02021   0.01111   0.0044   1.0000   0.2622
  -4.000  -0.5073   0.01956   0.01059   0.0060   1.0000   0.2717
  -3.750  -0.4884   0.01904   0.01008   0.0077   1.0000   0.2811
  -3.500  -0.4710   0.01861   0.00973   0.0097   1.0000   0.2904
  -3.250  -0.4544   0.01828   0.00947   0.0118   1.0000   0.2995
  -3.000  -0.4378   0.01806   0.00933   0.0138   1.0000   0.3114
  -2.750  -0.4224   0.01820   0.00972   0.0162   1.0000   0.3248
  -2.500  -0.4062   0.01900   0.01093   0.0186   1.0000   0.3387
  -2.250  -0.3886   0.02012   0.01236   0.0208   1.0000   0.3525
  -1.750  -0.3496   0.02331   0.01527   0.0240   1.0000   0.4376
  -1.500  -0.3348   0.02365   0.01553   0.0260   1.0000   0.4600
  -1.250  -0.3218   0.02340   0.01514   0.0280   1.0000   0.4856
  -1.000  -0.2872   0.02175   0.01330   0.0255   0.9911   0.5227
  -0.750  -0.2498   0.01974   0.01118   0.0225   0.9818   0.5500
  -0.500  -0.2103   0.01840   0.00981   0.0193   0.9711   0.5699
  -0.250  -0.1609   0.01718   0.00884   0.0146   0.9591   0.5882
   0.000  -0.0977   0.01611   0.00831   0.0081   0.9425   0.6072
   0.250  -0.0385   0.01547   0.00822   0.0031   0.9240   0.6293
   0.500   0.0153   0.01508   0.00805  -0.0008   0.9068   0.6589
   0.750   0.0658   0.01480   0.00778  -0.0044   0.8905   0.6863
   1.000   0.1108   0.01450   0.00753  -0.0068   0.8732   0.7057
   1.250   0.1541   0.01417   0.00727  -0.0088   0.8536   0.7168
   1.500   0.1945   0.01389   0.00702  -0.0102   0.8308   0.7257
   1.750   0.2308   0.01366   0.00683  -0.0107   0.8044   0.7343
   2.000   0.2634   0.01352   0.00669  -0.0106   0.7739   0.7427
   2.250   0.2929   0.01345   0.00661  -0.0099   0.7385   0.7507
   2.500   0.3206   0.01343   0.00655  -0.0087   0.6973   0.7605
   2.750   0.3446   0.01342   0.00652  -0.0070   0.6409   0.7728
   3.000   0.3673   0.01357   0.00641  -0.0048   0.5476   0.7880
   3.250   0.3907   0.01428   0.00658  -0.0033   0.4265   0.8080
   3.500   0.4254   0.01509   0.00698  -0.0046   0.3602   0.8420
   3.750   0.4639   0.01593   0.00755  -0.0068   0.3282   0.8797
   4.000   0.5032   0.01670   0.00821  -0.0091   0.3061   0.9147
   4.250   0.5396   0.01748   0.00888  -0.0108   0.2908   0.9422
   4.500   0.5717   0.01829   0.00956  -0.0117   0.2796   0.9635
   4.750   0.6023   0.01899   0.01035  -0.0122   0.2694   0.9780
   5.000   0.6311   0.01983   0.01104  -0.0125   0.2590   0.9864
   5.250   0.6581   0.02036   0.01168  -0.0125   0.2476   0.9947
   5.500   0.6857   0.02112   0.01243  -0.0126   0.2377   1.0000
   5.750   0.7075   0.02166   0.01300  -0.0114   0.2283   1.0000
   6.000   0.7291   0.02234   0.01371  -0.0103   0.2191   1.0000
   6.250   0.7501   0.02280   0.01415  -0.0091   0.2087   1.0000
   6.500   0.7701   0.02337   0.01487  -0.0077   0.1986   1.0000
   6.750   0.7918   0.02397   0.01536  -0.0066   0.1892   1.0000
   7.000   0.8101   0.02444   0.01608  -0.0049   0.1779   1.0000
   7.250   0.8282   0.02493   0.01661  -0.0032   0.1645   1.0000
   7.500   0.8443   0.02532   0.01707  -0.0011   0.1475   1.0000
   7.750   0.8595   0.02595   0.01772   0.0012   0.1295   1.0000
   8.000   0.8765   0.02699   0.01875   0.0031   0.1168   1.0000
   8.250   0.8953   0.02789   0.01952   0.0046   0.1086   1.0000
   8.500   0.9122   0.02939   0.02132   0.0065   0.1019   1.0000
   8.750   0.9306   0.03029   0.02220   0.0080   0.0966   1.0000
   9.000   0.9480   0.03195   0.02394   0.0095   0.0927   1.0000
   9.250   0.9622   0.03393   0.02627   0.0115   0.0896   1.0000
   9.500   0.9757   0.03587   0.02845   0.0135   0.0870   1.0000
   9.750   0.9899   0.03751   0.03024   0.0152   0.0847   1.0000
  10.000   1.0071   0.03923   0.03190   0.0163   0.0822   1.0000
  10.250   1.0100   0.04198   0.03504   0.0191   0.0808   1.0000
  10.500   1.0065   0.04504   0.03856   0.0222   0.0797   1.0000
  10.750   0.9974   0.04856   0.04250   0.0254   0.0791   1.0000
  11.000   0.9816   0.05237   0.04666   0.0286   0.0789   1.0000
  11.250   0.9574   0.05616   0.05072   0.0322   0.0790   1.0000
  11.500   0.9272   0.06039   0.05517   0.0347   0.0794   1.0000
  11.750   0.8920   0.06592   0.06090   0.0344   0.0800   1.0000
  12.000   0.8550   0.07317   0.06830   0.0310   0.0808   1.0000
  12.250   0.8228   0.08173   0.07693   0.0261   0.0816   1.0000
  12.500   0.7095   0.11496   0.11015   0.0053   0.0941   1.0000
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