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GOE 382 AIRFOIL (goe382-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 382 AIRFOIL (goe382-il)
Reynolds number: 100,000
Max Cl/Cd: 25.46 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe382-il-100000.txt
Download as CSV file: xf-goe382-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 382 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0374   0.10802   0.10320  -0.1029   0.9094   0.1415
 -10.250   0.0409   0.10562   0.10078  -0.1040   0.8986   0.1468
 -10.000   0.0147   0.10285   0.09804  -0.1083   0.8881   0.1511
  -9.750   0.0434   0.09984   0.09500  -0.1056   0.8779   0.1534
  -9.500   0.0573   0.09742   0.09255  -0.1046   0.8699   0.1576
  -9.250  -0.0089   0.09621   0.09141  -0.1133   0.8556   0.1657
  -9.000   0.0463   0.09200   0.08713  -0.1071   0.8516   0.1683
  -8.750   0.0658   0.08998   0.08509  -0.1054   0.8424   0.1727
  -8.500  -0.0144   0.08758   0.08274  -0.1155   0.8317   0.1823
  -8.250   0.0517   0.08445   0.07957  -0.1082   0.8263   0.1850
  -8.000   0.0706   0.08227   0.07737  -0.1067   0.8186   0.1887
  -7.750   0.0695   0.07971   0.07476  -0.1073   0.8130   0.1955
  -7.500   0.0393   0.07640   0.07156  -0.1110   0.8023   0.2020
  -7.250   0.0620   0.07392   0.06902  -0.1093   0.7970   0.2046
  -7.000   0.0662   0.07177   0.06686  -0.1089   0.7901   0.2087
  -6.750  -0.0872   0.05038   0.04397  -0.1190   0.7796   0.1128
  -6.500  -0.0819   0.04498   0.03783  -0.1174   0.7759   0.1023
  -6.250  -0.0818   0.04401   0.03667  -0.1140   0.7657   0.1003
  -6.000  -0.0613   0.04156   0.03395  -0.1133   0.7608   0.0986
  -5.750  -0.0357   0.03902   0.03100  -0.1130   0.7575   0.0977
  -5.500  -0.0333   0.03865   0.03045  -0.1097   0.7474   0.0978
  -5.250  -0.0081   0.03691   0.02836  -0.1091   0.7426   0.0983
  -5.000   0.0240   0.03501   0.02610  -0.1093   0.7392   0.0987
  -4.750   0.0313   0.03490   0.02586  -0.1065   0.7298   0.0989
  -4.500   0.0598   0.03366   0.02437  -0.1061   0.7247   0.0997
  -4.250   0.0953   0.03223   0.02267  -0.1066   0.7212   0.1011
  -4.000   0.1088   0.03208   0.02255  -0.1046   0.7129   0.1025
  -3.750   0.1337   0.03146   0.02199  -0.1040   0.7067   0.1056
  -3.500   0.1687   0.03046   0.02088  -0.1045   0.7030   0.1111
  -3.250   0.1893   0.03022   0.02074  -0.1034   0.6967   0.1156
  -3.000   0.2050   0.03029   0.02085  -0.1015   0.6885   0.1211
  -2.750   0.2387   0.02937   0.01996  -0.1018   0.6846   0.1322
  -2.500   0.2740   0.02825   0.01892  -0.1022   0.6816   0.1598
  -2.250   0.2691   0.02907   0.02005  -0.0979   0.6701   0.1888
  -2.000   0.2954   0.02753   0.01931  -0.0974   0.6662   0.3454
  -1.750   0.3234   0.02621   0.01885  -0.0964   0.6631   0.5454
  -1.500   0.3181   0.02749   0.02050  -0.0917   0.6517   0.6374
  -1.250   0.3444   0.02701   0.02038  -0.0891   0.6477   0.7649
  -1.000   0.3822   0.02666   0.02005  -0.0881   0.6447   0.8538
  -0.750   0.3945   0.02820   0.02168  -0.0860   0.6342   0.9035
  -0.500   0.4642   0.02797   0.02117  -0.0918   0.6299   0.9469
  -0.250   0.5492   0.02746   0.02028  -0.1010   0.6263   0.9665
   0.000   0.6153   0.02821   0.02090  -0.1091   0.6181   0.9869
   0.250   0.6798   0.02812   0.02059  -0.1164   0.6116   1.0000
   0.500   0.7002   0.02786   0.02015  -0.1154   0.6075   1.0000
   0.750   0.6830   0.02906   0.02138  -0.1093   0.5998   1.0000
   1.000   0.6789   0.02977   0.02204  -0.1048   0.5930   1.0000
   1.250   0.7056   0.02958   0.02167  -0.1045   0.5893   1.0000
   1.500   0.7435   0.02920   0.02105  -0.1057   0.5864   1.0000
   1.750   0.6791   0.03232   0.02437  -0.0930   0.5743   1.0000
   2.000   0.7188   0.03180   0.02367  -0.0944   0.5711   1.0000
   2.250   0.7632   0.03122   0.02287  -0.0965   0.5685   1.0000
   2.500   0.6802   0.03600   0.02788  -0.0824   0.5547   1.0000
   2.750   0.7293   0.03511   0.02682  -0.0849   0.5527   1.0000
   3.000   0.7791   0.03424   0.02577  -0.0875   0.5507   1.0000
   3.250   0.6181   0.04581   0.03769  -0.0695   0.5276   1.0000
   3.500   0.6792   0.04313   0.03484  -0.0713   0.5286   1.0000
   3.750   0.7477   0.04048   0.03200  -0.0746   0.5294   1.0000
   4.000   0.8352   0.03757   0.02887  -0.0811   0.5306   1.0000
   7.750   0.3304   0.11601   0.10886  -0.0409   0.4695   1.0000
   8.000   0.3501   0.11773   0.11053  -0.0409   0.4648   1.0000
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