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SG6042 (sg6042-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.51 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6042-il-1000000.txt
Download as CSV file: xf-sg6042-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6042                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2941   0.09340   0.09174  -0.0550   0.9926   0.0101
  -9.000  -0.2829   0.08931   0.08765  -0.0588   0.9906   0.0103
  -7.750  -0.2847   0.02202   0.01884  -0.1250   0.9570   0.0090
  -7.500  -0.2639   0.01936   0.01576  -0.1253   0.9509   0.0091
  -7.250  -0.2400   0.01618   0.01214  -0.1265   0.9470   0.0097
  -7.000  -0.2157   0.01542   0.01128  -0.1263   0.9409   0.0100
  -6.750  -0.1876   0.01480   0.01057  -0.1267   0.9362   0.0105
  -6.500  -0.1582   0.01380   0.00937  -0.1273   0.9321   0.0111
  -6.250  -0.1337   0.01305   0.00846  -0.1268   0.9253   0.0116
  -6.000  -0.1048   0.01257   0.00783  -0.1270   0.9203   0.0119
  -5.750  -0.0804   0.01116   0.00624  -0.1267   0.9145   0.0126
  -5.500  -0.0544   0.01058   0.00560  -0.1265   0.9085   0.0131
  -5.250  -0.0261   0.01018   0.00513  -0.1266   0.9037   0.0138
  -5.000   0.0000   0.00979   0.00469  -0.1263   0.8981   0.0145
  -4.750   0.0274   0.00959   0.00442  -0.1261   0.8927   0.0152
  -4.500   0.0542   0.00892   0.00365  -0.1260   0.8876   0.0160
  -4.250   0.0801   0.00855   0.00326  -0.1256   0.8820   0.0168
  -4.000   0.1074   0.00829   0.00295  -0.1255   0.8765   0.0177
  -3.750   0.1352   0.00806   0.00267  -0.1254   0.8715   0.0187
  -3.500   0.1620   0.00782   0.00239  -0.1252   0.8661   0.0199
  -3.250   0.1895   0.00759   0.00213  -0.1251   0.8611   0.0216
  -3.000   0.2174   0.00745   0.00195  -0.1250   0.8560   0.0235
  -2.750   0.2444   0.00725   0.00177  -0.1247   0.8502   0.0293
  -2.500   0.2719   0.00703   0.00162  -0.1246   0.8444   0.0549
  -2.250   0.2992   0.00689   0.00154  -0.1245   0.8388   0.0734
  -2.000   0.3265   0.00675   0.00145  -0.1244   0.8330   0.0949
  -1.750   0.3542   0.00659   0.00137  -0.1244   0.8274   0.1355
  -1.500   0.3808   0.00633   0.00131  -0.1242   0.8207   0.2022
  -1.250   0.4073   0.00597   0.00125  -0.1241   0.8136   0.3213
  -1.000   0.4331   0.00548   0.00123  -0.1240   0.8065   0.4894
  -0.750   0.4593   0.00520   0.00125  -0.1237   0.7995   0.6114
  -0.500   0.4861   0.00510   0.00128  -0.1234   0.7925   0.6691
  -0.250   0.5130   0.00507   0.00128  -0.1231   0.7842   0.7008
   0.000   0.5396   0.00503   0.00130  -0.1227   0.7752   0.7345
   0.250   0.5662   0.00503   0.00131  -0.1223   0.7661   0.7610
   0.500   0.5925   0.00501   0.00133  -0.1218   0.7553   0.7845
   0.750   0.6181   0.00500   0.00136  -0.1212   0.7432   0.8143
   1.000   0.6430   0.00499   0.00139  -0.1203   0.7300   0.8446
   1.250   0.6671   0.00500   0.00143  -0.1193   0.7166   0.8756
   1.500   0.6894   0.00500   0.00146  -0.1179   0.7018   0.9107
   1.750   0.7120   0.00500   0.00149  -0.1165   0.6840   0.9597
   2.000   0.7465   0.00514   0.00151  -0.1179   0.6598   1.0000
   2.250   0.7712   0.00530   0.00157  -0.1173   0.6357   1.0000
   2.500   0.7957   0.00549   0.00165  -0.1166   0.6133   1.0000
   2.750   0.8200   0.00569   0.00175  -0.1159   0.5884   1.0000
   3.000   0.8436   0.00594   0.00186  -0.1150   0.5590   1.0000
   3.250   0.8673   0.00619   0.00198  -0.1142   0.5306   1.0000
   3.500   0.8902   0.00648   0.00213  -0.1132   0.4980   1.0000
   3.750   0.9125   0.00683   0.00231  -0.1122   0.4613   1.0000
   4.000   0.9348   0.00719   0.00249  -0.1112   0.4237   1.0000
   4.250   0.9568   0.00757   0.00270  -0.1101   0.3874   1.0000
   4.500   0.9789   0.00795   0.00292  -0.1091   0.3512   1.0000
   4.750   1.0012   0.00833   0.00314  -0.1081   0.3190   1.0000
   5.000   1.0233   0.00871   0.00337  -0.1071   0.2884   1.0000
   5.250   1.0454   0.00910   0.00363  -0.1061   0.2592   1.0000
   5.500   1.0675   0.00948   0.00388  -0.1051   0.2341   1.0000
   5.750   1.0899   0.00984   0.00413  -0.1042   0.2113   1.0000
   6.000   1.1117   0.01023   0.00441  -0.1032   0.1899   1.0000
   6.250   1.1337   0.01059   0.00469  -0.1022   0.1702   1.0000
   6.500   1.1557   0.01096   0.00497  -0.1012   0.1542   1.0000
   6.750   1.1775   0.01132   0.00527  -0.1002   0.1398   1.0000
   7.000   1.1990   0.01168   0.00558  -0.0992   0.1263   1.0000
   7.250   1.2203   0.01205   0.00589  -0.0981   0.1145   1.0000
   7.500   1.2412   0.01243   0.00622  -0.0969   0.1034   1.0000
   7.750   1.2612   0.01283   0.00657  -0.0956   0.0937   1.0000
   8.000   1.2813   0.01316   0.00689  -0.0943   0.0870   1.0000
   8.250   1.3004   0.01354   0.00724  -0.0928   0.0796   1.0000
   8.500   1.3189   0.01394   0.00761  -0.0912   0.0729   1.0000
   8.750   1.3380   0.01431   0.00799  -0.0897   0.0675   1.0000
   9.000   1.3561   0.01474   0.00839  -0.0882   0.0624   1.0000
   9.250   1.3742   0.01517   0.00883  -0.0866   0.0578   1.0000
   9.500   1.3928   0.01556   0.00924  -0.0851   0.0544   1.0000
   9.750   1.4092   0.01609   0.00975  -0.0833   0.0498   1.0000
  10.000   1.4273   0.01650   0.01020  -0.0818   0.0473   1.0000
  10.250   1.4449   0.01696   0.01068  -0.0803   0.0447   1.0000
  10.500   1.4600   0.01756   0.01127  -0.0784   0.0411   1.0000
  10.750   1.4766   0.01807   0.01182  -0.0768   0.0389   1.0000
  11.000   1.4932   0.01858   0.01237  -0.0752   0.0365   1.0000
  11.250   1.5068   0.01929   0.01307  -0.0733   0.0334   1.0000
  11.500   1.5217   0.01991   0.01374  -0.0715   0.0313   1.0000
  11.750   1.5367   0.02053   0.01440  -0.0699   0.0292   1.0000
  12.000   1.5480   0.02141   0.01527  -0.0678   0.0262   1.0000
  12.250   1.5619   0.02213   0.01605  -0.0661   0.0249   1.0000
  12.500   1.5752   0.02289   0.01685  -0.0644   0.0233   1.0000
  12.750   1.5859   0.02386   0.01783  -0.0625   0.0217   1.0000
  13.000   1.5946   0.02499   0.01903  -0.0604   0.0203   1.0000
  13.250   1.6070   0.02586   0.01996  -0.0588   0.0197   1.0000
  13.500   1.6177   0.02687   0.02104  -0.0571   0.0189   1.0000
  13.750   1.6273   0.02799   0.02221  -0.0555   0.0179   1.0000
  14.000   1.6340   0.02937   0.02364  -0.0536   0.0169   1.0000
  14.250   1.6377   0.03104   0.02539  -0.0516   0.0161   1.0000
  14.500   1.6472   0.03226   0.02670  -0.0502   0.0158   1.0000
  14.750   1.6559   0.03358   0.02810  -0.0489   0.0153   1.0000
  15.000   1.6630   0.03508   0.02968  -0.0475   0.0148   1.0000
  15.250   1.6689   0.03673   0.03140  -0.0462   0.0143   1.0000
  15.500   1.6733   0.03857   0.03331  -0.0450   0.0138   1.0000
  15.750   1.6754   0.04069   0.03550  -0.0438   0.0133   1.0000
  16.000   1.6733   0.04335   0.03826  -0.0427   0.0129   1.0000
  16.250   1.6708   0.04617   0.04120  -0.0418   0.0126   1.0000
  16.500   1.6751   0.04836   0.04348  -0.0413   0.0124   1.0000
  16.750   1.6782   0.05073   0.04596  -0.0409   0.0121   1.0000
  17.000   1.6786   0.05354   0.04887  -0.0407   0.0119   1.0000
  17.250   1.6786   0.05650   0.05193  -0.0406   0.0116   1.0000
  17.500   1.6781   0.05964   0.05517  -0.0409   0.0113   1.0000
  17.750   1.6751   0.06322   0.05887  -0.0413   0.0111   1.0000
  18.000   1.6704   0.06719   0.06294  -0.0421   0.0108   1.0000
  18.250   1.6639   0.07159   0.06745  -0.0432   0.0107   1.0000
  18.500   1.6552   0.07651   0.07249  -0.0448   0.0104   1.0000
  18.750   1.6431   0.08218   0.07827  -0.0468   0.0102   1.0000
  19.000   1.6285   0.08847   0.08470  -0.0494   0.0101   1.0000
  19.250   1.6109   0.09557   0.09195  -0.0526   0.0099   1.0000
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