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GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 518 AIRFOIL (goe518-il)
Reynolds number: 100,000
Max Cl/Cd: 41.38 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe518-il-100000.txt
Download as CSV file: xf-goe518-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 518 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.0873   0.11095   0.10663  -0.0712   0.9189   0.1079
  -8.250  -0.1181   0.10896   0.10467  -0.0804   0.9088   0.1107
  -8.000  -0.1594   0.10741   0.10307  -0.0828   0.8929   0.1111
  -7.750  -0.0536   0.09975   0.09544  -0.0804   0.8949   0.1162
  -7.500  -0.0520   0.09711   0.09283  -0.0810   0.8834   0.1196
  -7.250  -0.0730   0.09459   0.09030  -0.0840   0.8723   0.1234
  -7.000  -0.1260   0.09351   0.08908  -0.0849   0.8524   0.1250
  -6.750  -0.0877   0.08783   0.08353  -0.0846   0.8484   0.1275
  -6.500  -0.0523   0.08403   0.07972  -0.0860   0.8445   0.1319
  -6.250  -0.0575   0.08163   0.07730  -0.0849   0.8314   0.1357
  -6.000  -0.0977   0.07986   0.07515  -0.0854   0.8148   0.1416
  -5.750  -0.0568   0.07451   0.07001  -0.0862   0.8116   0.1444
  -5.500  -0.0239   0.07075   0.06621  -0.0882   0.8083   0.1509
  -5.250  -0.0462   0.06909   0.06420  -0.0861   0.7929   0.1595
  -5.000  -0.0064   0.06444   0.05969  -0.0876   0.7907   0.1639
  -4.750  -0.0049   0.06285   0.05806  -0.0844   0.7774   0.1699
  -4.500   0.0199   0.05894   0.05400  -0.0858   0.7736   0.1826
  -4.250   0.0147   0.05804   0.05281  -0.0824   0.7597   0.1971
  -4.000   0.0521   0.05465   0.04942  -0.0838   0.7566   0.2127
  -3.750   0.0608   0.05181   0.04662  -0.0811   0.7458   0.2212
  -3.500   0.0902   0.04887   0.04359  -0.0815   0.7402   0.2419
  -2.500   0.2102   0.03495   0.02710  -0.0804   0.7073   0.1223
  -2.250   0.2691   0.03148   0.02288  -0.0839   0.7022   0.1092
  -2.000   0.2926   0.02994   0.02113  -0.0824   0.6888   0.1070
  -1.750   0.3404   0.02800   0.01881  -0.0849   0.6779   0.1051
  -1.500   0.4010   0.02628   0.01669  -0.0900   0.6661   0.1062
  -1.250   0.4309   0.02559   0.01575  -0.0897   0.6508   0.1088
  -1.000   0.4644   0.02497   0.01486  -0.0901   0.6357   0.1107
  -0.750   0.5016   0.02409   0.01390  -0.0914   0.6208   0.1137
  -0.500   0.5393   0.02353   0.01324  -0.0929   0.6065   0.1188
  -0.250   0.5733   0.02310   0.01269  -0.0937   0.5929   0.1276
   0.000   0.5882   0.02299   0.01260  -0.0911   0.5795   0.1373
   0.250   0.6146   0.02270   0.01226  -0.0905   0.5680   0.1550
   0.500   0.8702   0.02159   0.01272  -0.1352   0.5406   1.0000
   0.750   0.8897   0.02195   0.01287  -0.1337   0.5319   1.0000
   1.000   0.9055   0.02230   0.01308  -0.1315   0.5229   1.0000
   1.250   0.9299   0.02264   0.01319  -0.1310   0.5157   1.0000
   1.500   0.9398   0.02308   0.01359  -0.1278   0.5080   1.0000
   1.750   0.9651   0.02341   0.01371  -0.1274   0.5017   1.0000
   2.000   0.9822   0.02389   0.01411  -0.1256   0.4957   1.0000
   2.250   0.9943   0.02438   0.01457  -0.1228   0.4898   1.0000
   2.500   1.0184   0.02477   0.01480  -0.1223   0.4846   1.0000
   2.750   1.0453   0.02526   0.01512  -0.1224   0.4800   1.0000
   3.000   1.0500   0.02587   0.01581  -0.1183   0.4749   1.0000
   3.250   1.0648   0.02637   0.01627  -0.1161   0.4701   1.0000
   3.500   1.0914   0.02680   0.01655  -0.1161   0.4657   1.0000
   3.750   1.1169   0.02739   0.01701  -0.1160   0.4619   1.0000
   4.000   1.1189   0.02813   0.01787  -0.1115   0.4581   1.0000
   4.250   1.1280   0.02883   0.01861  -0.1084   0.4543   1.0000
   4.500   1.1444   0.02946   0.01921  -0.1066   0.4509   1.0000
   4.750   1.1696   0.03003   0.01968  -0.1065   0.4478   1.0000
   5.000   1.2043   0.03072   0.02022  -0.1082   0.4449   1.0000
   5.250   1.1956   0.03173   0.02142  -0.1020   0.4421   1.0000
   5.500   1.1921   0.03275   0.02255  -0.0969   0.4391   1.0000
   5.750   1.1950   0.03369   0.02355  -0.0929   0.4358   1.0000
   6.000   1.2067   0.03449   0.02435  -0.0905   0.4328   1.0000
   6.250   1.2276   0.03522   0.02505  -0.0898   0.4302   1.0000
   6.500   1.2580   0.03597   0.02572  -0.0908   0.4279   1.0000
   6.750   1.2559   0.03736   0.02720  -0.0863   0.4258   1.0000
   7.000   1.2122   0.03930   0.02936  -0.0749   0.4237   1.0000
   7.250   1.1483   0.04244   0.03277  -0.0619   0.4213   1.0000
   7.500   0.4594   0.11496   0.10703  -0.0405   0.4700   1.0000
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