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GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 369 AIRFOIL (goe369-il)
Reynolds number: 100,000
Max Cl/Cd: 59.23 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe369-il-100000.txt
Download as CSV file: xf-goe369-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 369 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3522   0.09983   0.09503  -0.0114   1.0000   0.0378
  -7.750  -0.3495   0.09795   0.09323  -0.0130   1.0000   0.0383
  -7.500  -0.3466   0.09651   0.09186  -0.0162   1.0000   0.0387
  -7.250  -0.3376   0.09501   0.09040  -0.0215   1.0000   0.0391
  -7.000  -0.3244   0.09320   0.08860  -0.0269   1.0000   0.0393
  -6.750  -0.3158   0.08853   0.08398  -0.0274   1.0000   0.0397
  -6.500  -0.3127   0.08283   0.07837  -0.0224   1.0000   0.0409
  -6.250  -0.3043   0.07940   0.07499  -0.0221   1.0000   0.0421
  -6.000  -0.2941   0.07638   0.07202  -0.0231   1.0000   0.0434
  -5.750  -0.2826   0.07347   0.06914  -0.0246   1.0000   0.0450
  -5.500  -0.2695   0.07063   0.06633  -0.0265   1.0000   0.0467
  -5.250  -0.2529   0.06802   0.06372  -0.0294   1.0000   0.0489
  -5.000  -0.2207   0.06743   0.06294  -0.0365   1.0000   0.0509
  -4.750  -0.2117   0.06429   0.05984  -0.0368   1.0000   0.0516
  -4.500  -0.2225   0.06164   0.05737  -0.0327   1.0000   0.0522
  -4.250  -0.2289   0.05970   0.05550  -0.0301   0.9987   0.0530
  -4.000  -0.1896   0.05536   0.05111  -0.0359   0.9892   0.0581
  -3.750  -0.1298   0.05172   0.04713  -0.0462   0.9786   0.0654
  -3.500  -0.0908   0.04768   0.04305  -0.0512   0.9699   0.0746
  -3.250  -0.0464   0.04390   0.03906  -0.0571   0.9592   0.0811
  -3.000   0.0012   0.04110   0.03594  -0.0627   0.9489   0.0926
  -2.750   0.0462   0.03757   0.03225  -0.0677   0.9422   0.1068
  -2.500   0.0816   0.03474   0.02930  -0.0706   0.9309   0.1231
  -2.250   0.1390   0.01343   0.00825  -0.0750   0.8950   0.1801
  -1.500   0.1967   0.02534   0.01992  -0.0750   0.8885   0.3584
  -1.250   0.2249   0.02339   0.01791  -0.0747   0.8770   0.4043
  -1.000   0.2684   0.02226   0.01629  -0.0769   0.8651   0.3800
  -0.750   0.3366   0.02202   0.01439  -0.0790   0.8547   0.1478
  -0.500   0.3681   0.02096   0.01294  -0.0777   0.8420   0.1152
  -0.250   0.3973   0.02000   0.01168  -0.0766   0.8301   0.0993
   0.000   0.4263   0.01952   0.01084  -0.0754   0.8190   0.0904
   0.250   0.4540   0.01885   0.01000  -0.0744   0.8088   0.0908
   0.500   0.4801   0.01799   0.00918  -0.0736   0.7978   0.0947
   0.750   0.5054   0.01750   0.00871  -0.0725   0.7865   0.0974
   1.000   0.5310   0.01717   0.00833  -0.0715   0.7758   0.1069
   1.250   0.5576   0.01694   0.00798  -0.0706   0.7658   0.1189
   1.500   0.5831   0.01669   0.00781  -0.0697   0.7541   0.1576
   1.750   0.6248   0.01504   0.00758  -0.0719   0.7411   1.0000
   2.000   0.6488   0.01527   0.00762  -0.0706   0.7274   1.0000
   2.250   0.6727   0.01547   0.00766  -0.0692   0.7128   1.0000
   2.500   0.6966   0.01562   0.00768  -0.0678   0.6974   1.0000
   2.750   0.7206   0.01576   0.00770  -0.0664   0.6820   1.0000
   3.000   0.7447   0.01589   0.00775  -0.0651   0.6667   1.0000
   3.250   0.7691   0.01605   0.00786  -0.0639   0.6518   1.0000
   3.500   0.7935   0.01620   0.00795  -0.0628   0.6366   1.0000
   3.750   0.8180   0.01630   0.00798  -0.0616   0.6205   1.0000
   4.000   0.8419   0.01636   0.00801  -0.0603   0.6020   1.0000
   4.250   0.8655   0.01637   0.00799  -0.0589   0.5809   1.0000
   4.500   0.8897   0.01633   0.00791  -0.0575   0.5607   1.0000
   4.750   0.9129   0.01636   0.00796  -0.0562   0.5367   1.0000
   5.000   0.9363   0.01638   0.00796  -0.0549   0.5117   1.0000
   5.250   0.9591   0.01643   0.00798  -0.0535   0.4821   1.0000
   5.500   0.9812   0.01657   0.00807  -0.0521   0.4473   1.0000
   5.750   1.0021   0.01692   0.00826  -0.0506   0.4056   1.0000
   6.000   1.0214   0.01760   0.00865  -0.0489   0.3602   1.0000
   6.250   1.0401   0.01856   0.00932  -0.0474   0.3176   1.0000
   6.500   1.0594   0.01958   0.01011  -0.0461   0.2834   1.0000
   6.750   1.0795   0.02059   0.01096  -0.0449   0.2577   1.0000
   7.000   1.1005   0.02158   0.01191  -0.0438   0.2361   1.0000
   7.250   1.1215   0.02260   0.01285  -0.0429   0.2191   1.0000
   7.500   1.1430   0.02369   0.01388  -0.0420   0.2049   1.0000
   7.750   1.1650   0.02486   0.01509  -0.0412   0.1930   1.0000
   8.000   1.1869   0.02611   0.01637  -0.0404   0.1823   1.0000
   8.250   1.2104   0.02757   0.01769  -0.0400   0.1731   1.0000
   8.500   1.2315   0.02883   0.01924  -0.0390   0.1647   1.0000
   8.750   1.2539   0.03045   0.02092  -0.0385   0.1569   1.0000
   9.000   1.2742   0.03179   0.02246  -0.0376   0.1490   1.0000
   9.250   1.2957   0.03372   0.02453  -0.0369   0.1430   1.0000
   9.500   1.3143   0.03546   0.02662  -0.0358   0.1372   1.0000
   9.750   1.3367   0.03756   0.02873  -0.0355   0.1321   1.0000
  10.000   1.3492   0.03983   0.03158  -0.0337   0.1276   1.0000
  10.250   1.3654   0.04157   0.03358  -0.0325   0.1219   1.0000
  10.500   1.3823   0.04413   0.03625  -0.0318   0.1172   1.0000
  10.750   1.3869   0.04584   0.03850  -0.0294   0.1109   1.0000
  11.000   1.4000   0.04632   0.03897  -0.0283   0.1020   1.0000
  11.250   1.4156   0.04650   0.03911  -0.0272   0.0933   1.0000
  11.500   1.4116   0.04892   0.04204  -0.0245   0.0876   1.0000
  11.750   1.4231   0.04986   0.04283  -0.0233   0.0788   1.0000
  12.000   1.4083   0.05234   0.04583  -0.0197   0.0740   1.0000
  12.250   1.4105   0.05338   0.04670  -0.0177   0.0663   1.0000
  12.500   1.3893   0.05657   0.05031  -0.0145   0.0642   1.0000
  12.750   1.3714   0.06001   0.05404  -0.0130   0.0614   1.0000
  13.000   1.3766   0.06190   0.05571  -0.0123   0.0556   1.0000
  13.250   1.3550   0.06652   0.06067  -0.0124   0.0551   1.0000
  13.500   1.3324   0.07193   0.06638  -0.0136   0.0548   1.0000
  13.750   1.3089   0.07799   0.07270  -0.0157   0.0547   1.0000
  14.000   1.2851   0.08468   0.07961  -0.0186   0.0550   1.0000
  14.250   1.2608   0.09206   0.08716  -0.0223   0.0554   1.0000
  14.500   1.2365   0.10001   0.09525  -0.0266   0.0558   1.0000
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