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GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 362 AIRFOIL (goe362-il)
Reynolds number: 50,000
Max Cl/Cd: 37.28 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe362-il-50000.txt
Download as CSV file: xf-goe362-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 362 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2548   0.10251   0.09606  -0.0226   1.0000   0.1315
  -8.500  -0.2571   0.10070   0.09433  -0.0234   1.0000   0.1353
  -8.250  -0.3277   0.10726   0.10043  -0.0196   1.0000   0.1285
  -8.000  -0.3242   0.10496   0.09817  -0.0200   1.0000   0.1329
  -7.750  -0.3315   0.10455   0.09790  -0.0211   1.0000   0.1361
  -7.500  -0.3420   0.10516   0.09869  -0.0240   1.0000   0.1371
  -7.250  -0.3188   0.09753   0.09103  -0.0200   1.0000   0.1426
  -7.000  -0.3186   0.09555   0.08915  -0.0200   1.0000   0.1479
  -6.750  -0.3257   0.09590   0.08966  -0.0245   1.0000   0.1513
  -6.500  -0.3144   0.09059   0.08440  -0.0209   1.0000   0.1553
  -6.250  -0.3105   0.08821   0.08211  -0.0210   1.0000   0.1625
  -6.000  -0.3106   0.08699   0.08100  -0.0252   1.0000   0.1669
  -5.750  -0.3030   0.08299   0.07707  -0.0209   1.0000   0.1745
  -5.500  -0.3005   0.08151   0.07568  -0.0251   1.0000   0.1817
  -5.250  -0.2955   0.07822   0.07246  -0.0216   1.0000   0.1908
  -4.750  -0.2825   0.07398   0.06830  -0.0263   1.0000   0.2101
  -4.500  -0.2798   0.07067   0.06508  -0.0219   1.0000   0.2176
  -4.250  -0.2722   0.06810   0.06255  -0.0227   1.0000   0.2284
  -4.000  -0.2635   0.06557   0.06005  -0.0234   1.0000   0.2419
  -3.750  -0.2546   0.06300   0.05752  -0.0234   1.0000   0.2570
  -3.500  -0.2455   0.06051   0.05506  -0.0230   1.0000   0.2743
  -3.250  -0.2337   0.05807   0.05264  -0.0238   1.0000   0.2993
  -3.000  -0.2258   0.05571   0.05033  -0.0224   1.0000   0.3288
  -2.750  -0.2220   0.05342   0.04812  -0.0190   1.0000   0.3637
  -1.500   0.0253   0.03575   0.02798  -0.0615   1.0000   0.1776
  -1.250   0.0604   0.03325   0.02488  -0.0638   1.0000   0.1627
  -1.000   0.0892   0.03177   0.02285  -0.0649   1.0000   0.1653
  -0.750   0.1133   0.03051   0.02138  -0.0654   1.0000   0.1703
  -0.500   0.1465   0.02960   0.01998  -0.0671   0.9967   0.1812
  -0.250   0.2046   0.02852   0.01855  -0.0730   0.9833   0.2073
   0.000   0.2633   0.02760   0.01737  -0.0787   0.9685   0.2603
   0.250   0.3197   0.02662   0.01664  -0.0841   0.9531   0.3612
   0.500   0.3729   0.02451   0.01574  -0.0882   0.9371   1.0000
   0.750   0.4232   0.02515   0.01580  -0.0925   0.9170   1.0000
   1.000   0.4769   0.02563   0.01595  -0.0972   0.8984   1.0000
   1.250   0.5182   0.02609   0.01621  -0.0997   0.8775   1.0000
   1.500   0.5653   0.02638   0.01635  -0.1030   0.8586   1.0000
   1.750   0.6133   0.02652   0.01638  -0.1059   0.8413   1.0000
   2.000   0.6556   0.02665   0.01644  -0.1077   0.8240   1.0000
   2.250   0.6853   0.02710   0.01685  -0.1076   0.8043   1.0000
   2.500   0.7196   0.02735   0.01707  -0.1080   0.7868   1.0000
   2.750   0.7529   0.02759   0.01729  -0.1081   0.7702   1.0000
   3.000   0.7849   0.02784   0.01756  -0.1078   0.7541   1.0000
   3.250   0.8153   0.02812   0.01784  -0.1073   0.7383   1.0000
   3.500   0.8443   0.02845   0.01819  -0.1066   0.7228   1.0000
   3.750   0.8699   0.02900   0.01881  -0.1056   0.7068   1.0000
   4.000   0.8933   0.02970   0.01957  -0.1046   0.6906   1.0000
   4.250   0.9175   0.03037   0.02030  -0.1035   0.6749   1.0000
   4.500   0.9417   0.03106   0.02107  -0.1024   0.6596   1.0000
   4.750   0.9656   0.03179   0.02188  -0.1013   0.6444   1.0000
   5.000   0.9891   0.03255   0.02279  -0.1002   0.6292   1.0000
   5.250   1.0123   0.03336   0.02372  -0.0990   0.6141   1.0000
   5.500   1.0352   0.03419   0.02468  -0.0978   0.5987   1.0000
   5.750   1.0577   0.03506   0.02568  -0.0965   0.5833   1.0000
   6.000   1.0806   0.03584   0.02667  -0.0951   0.5674   1.0000
   6.250   1.1050   0.03637   0.02735  -0.0936   0.5508   1.0000
   6.500   1.1342   0.03587   0.02691  -0.0913   0.5304   1.0000
   6.750   1.1610   0.03511   0.02626  -0.0886   0.5052   1.0000
   7.000   1.1841   0.03487   0.02611  -0.0861   0.4796   1.0000
   7.250   1.2086   0.03461   0.02592  -0.0838   0.4538   1.0000
   7.500   1.2321   0.03442   0.02578  -0.0813   0.4246   1.0000
   7.750   1.2543   0.03421   0.02559  -0.0786   0.3899   1.0000
   8.000   1.2712   0.03434   0.02568  -0.0755   0.3478   1.0000
   8.250   1.2870   0.03452   0.02556  -0.0722   0.3007   1.0000
   8.500   1.2995   0.03574   0.02662  -0.0692   0.2601   1.0000
   8.750   1.3142   0.03725   0.02789  -0.0669   0.2285   1.0000
   9.000   1.3297   0.03944   0.03010  -0.0649   0.2042   1.0000
   9.250   1.3430   0.04172   0.03246  -0.0629   0.1827   1.0000
   9.500   1.3574   0.04399   0.03467  -0.0610   0.1629   1.0000
   9.750   1.3699   0.04672   0.03739  -0.0592   0.1453   1.0000
  10.000   1.3800   0.04991   0.04077  -0.0572   0.1313   1.0000
  10.250   1.3911   0.05333   0.04428  -0.0556   0.1192   1.0000
  10.500   1.3900   0.05717   0.04869  -0.0529   0.1129   1.0000
  10.750   1.4011   0.06163   0.05322  -0.0517   0.1064   1.0000
  11.000   1.3878   0.06591   0.05807  -0.0488   0.1045   1.0000
  11.250   1.3713   0.07026   0.06285  -0.0463   0.1032   1.0000
  11.500   1.3496   0.07453   0.06742  -0.0439   0.1029   1.0000
  11.750   1.3251   0.07927   0.07241  -0.0425   0.1034   1.0000
  12.000   1.2994   0.08479   0.07815  -0.0427   0.1044   1.0000
  12.250   1.2740   0.09110   0.08462  -0.0442   0.1055   1.0000
  12.500   1.2503   0.09813   0.09177  -0.0468   0.1066   1.0000
  12.750   1.2289   0.10580   0.09952  -0.0500   0.1074   1.0000
  13.000   1.0346   0.16037   0.15347  -0.0953   0.1928   1.0000
  13.250   1.0567   0.16188   0.15514  -0.0921   0.1748   1.0000
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