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S5010 (s5010-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S5010 (s5010-il)
Reynolds number: 100,000
Max Cl/Cd: 45 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s5010-il-100000.txt
Download as CSV file: xf-s5010-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S5010                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4339   0.10562   0.10168   0.0148   1.0000   0.0958
  -9.000  -0.4446   0.10182   0.09793   0.0107   1.0000   0.0993
  -8.750  -0.4663   0.09817   0.09437   0.0046   1.0000   0.1004
  -8.500  -0.4371   0.09243   0.08863   0.0083   1.0000   0.1038
  -8.250  -0.4287   0.08854   0.08475   0.0078   1.0000   0.1085
  -8.000  -0.4389   0.08429   0.08059   0.0037   1.0000   0.1130
  -7.750  -0.5184   0.08764   0.08366   0.0063   1.0000   0.1059
  -7.500  -0.5184   0.08389   0.07998   0.0033   1.0000   0.1101
  -7.250  -0.5476   0.07926   0.07510  -0.0123   1.0000   0.1149
  -7.000  -0.5172   0.07444   0.07059  -0.0059   1.0000   0.1187
  -6.750  -0.5261   0.07097   0.06672  -0.0157   1.0000   0.1293
  -6.500  -0.5012   0.06580   0.06189  -0.0124   1.0000   0.1328
  -6.250  -0.4940   0.06165   0.05754  -0.0172   1.0000   0.1451
  -6.000  -0.4799   0.05842   0.05419  -0.0195   1.0000   0.1590
  -5.750  -0.4626   0.05497   0.05080  -0.0201   1.0000   0.1741
  -5.500  -0.4466   0.05202   0.04797  -0.0197   1.0000   0.1903
  -5.250  -0.4493   0.05035   0.04626  -0.0181   1.0000   0.2040
  -5.000  -0.3428   0.01915   0.01331  -0.0349   0.9588   0.0835
  -4.750  -0.3535   0.03112   0.02405  -0.0292   0.9696   0.0717
  -4.500  -0.3140   0.02755   0.02004  -0.0316   0.9565   0.0699
  -4.250  -0.2765   0.02551   0.01744  -0.0329   0.9426   0.0718
  -4.000  -0.2434   0.02356   0.01509  -0.0332   0.9283   0.0720
  -3.750  -0.2144   0.02198   0.01325  -0.0326   0.9140   0.0734
  -3.500  -0.1895   0.02067   0.01199  -0.0318   0.8998   0.0793
  -3.250  -0.1649   0.01986   0.01106  -0.0304   0.8860   0.0847
  -3.000  -0.1425   0.01884   0.01010  -0.0288   0.8727   0.0907
  -2.750  -0.1211   0.01810   0.00937  -0.0271   0.8598   0.1034
  -2.500  -0.1008   0.01719   0.00866  -0.0253   0.8475   0.1395
  -2.250  -0.0942   0.01408   0.00834  -0.0204   0.8372   0.7052
  -2.000   0.0468   0.01392   0.00811  -0.0368   0.8302   1.0000
  -1.750   0.0649   0.01395   0.00791  -0.0355   0.8169   1.0000
  -1.500   0.0840   0.01402   0.00777  -0.0342   0.8042   1.0000
  -1.250   0.1038   0.01413   0.00766  -0.0328   0.7922   1.0000
  -1.000   0.1237   0.01425   0.00758  -0.0313   0.7810   1.0000
  -0.750   0.1440   0.01438   0.00752  -0.0298   0.7699   1.0000
  -0.500   0.1665   0.01453   0.00752  -0.0289   0.7578   1.0000
  -0.250   0.1890   0.01470   0.00755  -0.0279   0.7463   1.0000
   0.000   0.2110   0.01487   0.00757  -0.0266   0.7354   1.0000
   0.250   0.2324   0.01500   0.00754  -0.0251   0.7256   1.0000
   0.500   0.2562   0.01518   0.00762  -0.0243   0.7135   1.0000
   0.750   0.2797   0.01537   0.00772  -0.0234   0.7019   1.0000
   1.000   0.3029   0.01554   0.00778  -0.0223   0.6911   1.0000
   1.250   0.3253   0.01564   0.00775  -0.0207   0.6816   1.0000
   1.500   0.3497   0.01583   0.00789  -0.0200   0.6693   1.0000
   1.750   0.3739   0.01602   0.00802  -0.0192   0.6575   1.0000
   2.000   0.3978   0.01618   0.00812  -0.0182   0.6463   1.0000
   2.250   0.4212   0.01627   0.00810  -0.0168   0.6364   1.0000
   2.500   0.4456   0.01641   0.00820  -0.0159   0.6243   1.0000
   2.750   0.4702   0.01659   0.00835  -0.0152   0.6117   1.0000
   3.000   0.4947   0.01674   0.00848  -0.0143   0.5994   1.0000
   3.250   0.5192   0.01688   0.00860  -0.0134   0.5873   1.0000
   3.500   0.5438   0.01698   0.00865  -0.0123   0.5754   1.0000
   3.750   0.5683   0.01704   0.00862  -0.0112   0.5639   1.0000
   4.000   0.5932   0.01717   0.00876  -0.0104   0.5505   1.0000
   4.250   0.6182   0.01731   0.00890  -0.0096   0.5366   1.0000
   4.500   0.6433   0.01745   0.00903  -0.0088   0.5224   1.0000
   4.750   0.6683   0.01759   0.00915  -0.0080   0.5080   1.0000
   5.000   0.6934   0.01773   0.00930  -0.0072   0.4931   1.0000
   5.250   0.7185   0.01788   0.00942  -0.0064   0.4780   1.0000
   5.500   0.7435   0.01806   0.00959  -0.0056   0.4620   1.0000
   5.750   0.7684   0.01832   0.00989  -0.0050   0.4445   1.0000
   6.000   0.7932   0.01856   0.01018  -0.0043   0.4269   1.0000
   6.250   0.8180   0.01882   0.01043  -0.0036   0.4095   1.0000
   6.500   0.8427   0.01909   0.01065  -0.0029   0.3921   1.0000
   6.750   0.8670   0.01947   0.01104  -0.0023   0.3737   1.0000
   7.000   0.8910   0.01989   0.01154  -0.0017   0.3542   1.0000
   7.250   0.9149   0.02033   0.01194  -0.0010   0.3357   1.0000
   7.500   0.9383   0.02085   0.01244  -0.0004   0.3170   1.0000
   7.750   0.9611   0.02147   0.01312   0.0002   0.2973   1.0000
   8.000   0.9837   0.02209   0.01374   0.0009   0.2787   1.0000
   8.250   1.0060   0.02283   0.01442   0.0015   0.2609   1.0000
   8.500   1.0271   0.02366   0.01537   0.0021   0.2422   1.0000
   8.750   1.0480   0.02454   0.01628   0.0028   0.2249   1.0000
   9.000   1.0684   0.02548   0.01723   0.0035   0.2084   1.0000
   9.250   1.0883   0.02649   0.01823   0.0043   0.1929   1.0000
   9.500   1.1076   0.02762   0.01937   0.0050   0.1782   1.0000
   9.750   1.1259   0.02882   0.02059   0.0058   0.1641   1.0000
  10.000   1.1430   0.03011   0.02197   0.0067   0.1511   1.0000
  10.250   1.1587   0.03148   0.02348   0.0076   0.1388   1.0000
  10.500   1.1731   0.03304   0.02523   0.0087   0.1277   1.0000
  10.750   1.1869   0.03473   0.02701   0.0097   0.1177   1.0000
  11.000   1.2014   0.03636   0.02861   0.0106   0.1079   1.0000
  11.250   1.2105   0.03795   0.03038   0.0118   0.0993   1.0000
  11.500   1.2161   0.04009   0.03274   0.0132   0.0915   1.0000
  11.750   1.2274   0.04202   0.03454   0.0141   0.0834   1.0000
  12.000   1.2196   0.04405   0.03697   0.0161   0.0782   1.0000
  12.250   1.2262   0.04610   0.03886   0.0172   0.0713   1.0000
  12.500   1.2132   0.04873   0.04186   0.0185   0.0683   1.0000
  12.750   1.2052   0.05135   0.04466   0.0189   0.0643   1.0000
  13.000   1.2055   0.05424   0.04748   0.0193   0.0592   1.0000
  13.250   1.1911   0.05815   0.05172   0.0187   0.0575   1.0000
  13.500   1.1763   0.06246   0.05630   0.0176   0.0555   1.0000
  13.750   1.1624   0.06706   0.06115   0.0161   0.0540   1.0000
  14.000   1.1512   0.07148   0.06570   0.0144   0.0521   1.0000
  14.250   0.8941   0.13260   0.12752  -0.0241   0.0953   1.0000
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