Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 367 AIRFOIL (goe367-il)
Reynolds number: 500,000
Max Cl/Cd: 93.25 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe367-il-500000.txt
Download as CSV file: xf-goe367-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 367 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2459   0.10779   0.10530  -0.0769   0.9824   0.0472
 -11.750  -0.5435   0.04235   0.03909  -0.1201   0.9487   0.0402
 -11.500  -0.5852   0.03774   0.03405  -0.1154   0.9297   0.0402
 -11.250  -0.6025   0.03422   0.03008  -0.1118   0.9178   0.0405
 -11.000  -0.6046   0.03179   0.02727  -0.1090   0.9074   0.0408
 -10.750  -0.5979   0.03015   0.02528  -0.1068   0.8990   0.0412
 -10.500  -0.5908   0.02778   0.02259  -0.1048   0.8906   0.0415
 -10.250  -0.5757   0.02604   0.02070  -0.1036   0.8840   0.0419
 -10.000  -0.5564   0.02499   0.01956  -0.1027   0.8767   0.0423
  -9.750  -0.5360   0.02411   0.01856  -0.1019   0.8704   0.0428
  -9.500  -0.5148   0.02328   0.01763  -0.1011   0.8637   0.0432
  -9.250  -0.4932   0.02246   0.01669  -0.1003   0.8564   0.0437
  -9.000  -0.4714   0.02163   0.01568  -0.0995   0.8498   0.0443
  -8.750  -0.4489   0.02083   0.01475  -0.0988   0.8427   0.0449
  -8.500  -0.4257   0.02015   0.01390  -0.0982   0.8367   0.0457
  -8.250  -0.4017   0.01960   0.01315  -0.0976   0.8314   0.0463
  -8.000  -0.3776   0.01893   0.01234  -0.0971   0.8255   0.0468
  -7.750  -0.3536   0.01773   0.01109  -0.0967   0.8201   0.0476
  -7.500  -0.3281   0.01716   0.01045  -0.0964   0.8152   0.0483
  -7.250  -0.3024   0.01667   0.00994  -0.0962   0.8100   0.0491
  -7.000  -0.2765   0.01621   0.00942  -0.0959   0.8047   0.0499
  -6.750  -0.2503   0.01578   0.00890  -0.0956   0.7998   0.0509
  -6.500  -0.2237   0.01542   0.00845  -0.0954   0.7951   0.0518
  -6.250  -0.1970   0.01517   0.00812  -0.0952   0.7900   0.0527
  -6.000  -0.1721   0.01435   0.00731  -0.0949   0.7850   0.0541
  -5.750  -0.1457   0.01398   0.00691  -0.0946   0.7804   0.0553
  -5.500  -0.1191   0.01367   0.00657  -0.0944   0.7756   0.0566
  -5.250  -0.0925   0.01336   0.00623  -0.0942   0.7705   0.0580
  -5.000  -0.0655   0.01312   0.00592  -0.0940   0.7655   0.0592
  -4.750  -0.0400   0.01266   0.00543  -0.0936   0.7608   0.0612
  -4.500  -0.0137   0.01239   0.00520  -0.0934   0.7557   0.0633
  -4.250   0.0132   0.01217   0.00495  -0.0932   0.7502   0.0656
  -4.000   0.0397   0.01190   0.00463  -0.0929   0.7451   0.0680
  -3.750   0.0661   0.01166   0.00442  -0.0926   0.7393   0.0711
  -3.500   0.0928   0.01147   0.00421  -0.0924   0.7324   0.0745
  -3.250   0.1196   0.01128   0.00401  -0.0921   0.7261   0.0796
  -3.000   0.1463   0.01111   0.00388  -0.0919   0.7197   0.0864
  -2.750   0.1734   0.01096   0.00377  -0.0917   0.7135   0.0963
  -2.500   0.2009   0.01088   0.00368  -0.0916   0.7078   0.1092
  -2.250   0.2284   0.01081   0.00365  -0.0916   0.7014   0.1204
  -2.000   0.2555   0.01072   0.00358  -0.0914   0.6949   0.1303
  -1.750   0.2830   0.01067   0.00349  -0.0914   0.6890   0.1377
  -1.500   0.3100   0.01056   0.00343  -0.0912   0.6820   0.1453
  -1.250   0.3373   0.01053   0.00335  -0.0911   0.6749   0.1513
  -1.000   0.3639   0.01040   0.00326  -0.0909   0.6676   0.1595
  -0.750   0.3908   0.01034   0.00318  -0.0907   0.6594   0.1663
  -0.500   0.4172   0.01024   0.00310  -0.0904   0.6517   0.1765
  -0.250   0.4436   0.01014   0.00304  -0.0902   0.6429   0.1905
   0.000   0.4692   0.00999   0.00298  -0.0898   0.6347   0.2230
   0.250   0.4881   0.00917   0.00295  -0.0886   0.6256   0.4692
   0.500   0.4959   0.00811   0.00315  -0.0841   0.6175   0.8418
   0.750   0.5172   0.00825   0.00334  -0.0822   0.6077   0.9028
   1.000   0.5386   0.00846   0.00352  -0.0802   0.5983   0.9298
   1.250   0.5614   0.00868   0.00369  -0.0786   0.5881   0.9491
   1.500   0.5964   0.00894   0.00389  -0.0798   0.5776   0.9623
   1.750   0.6436   0.00924   0.00408  -0.0837   0.5666   0.9705
   2.000   0.6952   0.00949   0.00423  -0.0888   0.5546   0.9753
   2.250   0.7318   0.00968   0.00435  -0.0908   0.5440   0.9811
   2.500   0.7846   0.00990   0.00446  -0.0963   0.5319   0.9849
   2.750   0.8287   0.01010   0.00456  -0.1000   0.5192   0.9897
   3.000   0.8700   0.01025   0.00466  -0.1031   0.5072   0.9938
   3.250   0.9158   0.01040   0.00472  -0.1072   0.4963   0.9975
   3.500   0.9536   0.01053   0.00480  -0.1097   0.4864   1.0000
   3.750   0.9743   0.01068   0.00490  -0.1085   0.4786   1.0000
   4.000   0.9947   0.01081   0.00502  -0.1072   0.4703   1.0000
   4.250   1.0138   0.01099   0.00514  -0.1057   0.4626   1.0000
   4.500   1.0333   0.01112   0.00527  -0.1042   0.4545   1.0000
   4.750   1.0503   0.01133   0.00542  -0.1023   0.4468   1.0000
   5.000   1.0686   0.01146   0.00555  -0.1006   0.4391   1.0000
   5.250   1.0835   0.01167   0.00571  -0.0983   0.4317   1.0000
   5.500   1.0993   0.01182   0.00586  -0.0961   0.4246   1.0000
   5.750   1.1124   0.01200   0.00603  -0.0934   0.4176   1.0000
   6.000   1.1233   0.01220   0.00620  -0.0902   0.4115   1.0000
   6.250   1.1343   0.01233   0.00634  -0.0871   0.4054   1.0000
   6.500   1.1382   0.01250   0.00649  -0.0825   0.3994   1.0000
   6.750   1.1381   0.01263   0.00662  -0.0771   0.3943   1.0000
   7.000   1.1467   0.01278   0.00677  -0.0735   0.3887   1.0000
   7.250   1.1596   0.01303   0.00701  -0.0709   0.3831   1.0000
   7.500   1.1761   0.01333   0.00729  -0.0691   0.3782   1.0000
   7.750   1.1958   0.01357   0.00757  -0.0680   0.3734   1.0000
   8.000   1.2148   0.01388   0.00788  -0.0667   0.3685   1.0000
   8.250   1.2324   0.01428   0.00825  -0.0653   0.3637   1.0000
   8.500   1.2531   0.01458   0.00859  -0.0645   0.3595   1.0000
   8.750   1.2730   0.01491   0.00895  -0.0635   0.3544   1.0000
   9.000   1.2908   0.01535   0.00937  -0.0623   0.3491   1.0000
   9.250   1.3096   0.01577   0.00981  -0.0613   0.3444   1.0000
   9.500   1.3298   0.01613   0.01023  -0.0605   0.3396   1.0000
   9.750   1.3473   0.01662   0.01072  -0.0593   0.3338   1.0000
  10.000   1.3640   0.01716   0.01127  -0.0582   0.3276   1.0000
  10.250   1.3820   0.01766   0.01181  -0.0572   0.3203   1.0000
  10.500   1.3960   0.01837   0.01249  -0.0557   0.3128   1.0000
  10.750   1.4134   0.01893   0.01310  -0.0548   0.3039   1.0000
  11.000   1.4270   0.01972   0.01387  -0.0535   0.2957   1.0000
  11.250   1.4425   0.02043   0.01462  -0.0524   0.2858   1.0000
  11.500   1.4556   0.02130   0.01549  -0.0511   0.2741   1.0000
  11.750   1.4650   0.02243   0.01657  -0.0495   0.2570   1.0000
  12.000   1.4646   0.02425   0.01824  -0.0471   0.2245   1.0000
  12.250   1.4462   0.02741   0.02110  -0.0433   0.1796   1.0000
  12.500   1.4410   0.02981   0.02341  -0.0409   0.1620   1.0000
  12.750   1.4400   0.03198   0.02556  -0.0390   0.1500   1.0000
  13.000   1.4407   0.03410   0.02766  -0.0374   0.1377   1.0000
  13.250   1.4416   0.03628   0.02981  -0.0360   0.1213   1.0000
  13.750   1.4331   0.04178   0.03518  -0.0331   0.0947   1.0000
  14.000   1.4315   0.04444   0.03786  -0.0320   0.0898   1.0000
  14.250   1.4316   0.04701   0.04049  -0.0312   0.0869   1.0000
  14.500   1.4288   0.04994   0.04346  -0.0304   0.0843   1.0000
  14.750   1.4241   0.05316   0.04673  -0.0296   0.0818   1.0000
  15.000   1.4219   0.05620   0.04984  -0.0291   0.0797   1.0000
  15.250   1.4235   0.05888   0.05262  -0.0288   0.0778   1.0000
  15.500   1.4216   0.06198   0.05580  -0.0285   0.0757   1.0000
  15.750   1.4159   0.06556   0.05944  -0.0282   0.0736   1.0000
  16.000   1.4061   0.06969   0.06363  -0.0280   0.0715   1.0000
  16.250   1.4087   0.07241   0.06645  -0.0280   0.0695   1.0000
  16.500   1.4109   0.07519   0.06931  -0.0281   0.0670   1.0000
  16.750   1.4081   0.07861   0.07278  -0.0282   0.0647   1.0000
  17.000   1.3989   0.08284   0.07705  -0.0284   0.0625   1.0000
  17.250   1.4060   0.08509   0.07941  -0.0287   0.0595   1.0000
  17.500   1.4053   0.08835   0.08271  -0.0290   0.0565   1.0000
  17.750   1.4027   0.09185   0.08625  -0.0295   0.0539   1.0000
  18.000   1.4035   0.09493   0.08939  -0.0299   0.0507   1.0000
  18.250   1.3989   0.09875   0.09323  -0.0305   0.0483   1.0000
  18.500   1.3984   0.10201   0.09655  -0.0310   0.0457   1.0000
  18.750   1.3947   0.10578   0.10035  -0.0318   0.0436   1.0000
  19.000   1.3894   0.10976   0.10436  -0.0326   0.0418   1.0000
<< Back to GOE 367 AIRFOIL (goe367-il)

Polar data table (+)

Polar graphs


<< Back to GOE 367 AIRFOIL (goe367-il)