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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 50,000
Max Cl/Cd: 37.65 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe100-il-50000.txt
Download as CSV file: xf-goe100-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 100 (SOPWITH) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4079   0.10620   0.09964  -0.0150   1.0000   0.1463
  -7.750  -0.4182   0.10524   0.09882  -0.0168   1.0000   0.1498
  -7.500  -0.4158   0.10155   0.09523  -0.0171   1.0000   0.1526
  -7.250  -0.4068   0.09765   0.09135  -0.0159   1.0000   0.1596
  -7.000  -0.4156   0.09680   0.09062  -0.0206   1.0000   0.1640
  -6.500  -0.4067   0.08998   0.08393  -0.0207   1.0000   0.1773
  -6.000  -0.3997   0.08430   0.07835  -0.0236   1.0000   0.1921
  -5.750  -0.3905   0.07954   0.07362  -0.0191   1.0000   0.2009
  -5.500  -0.3857   0.07635   0.07048  -0.0194   1.0000   0.2104
  -5.250  -0.3800   0.07336   0.06750  -0.0201   1.0000   0.2224
  -5.000  -0.3731   0.07024   0.06441  -0.0199   1.0000   0.2362
  -4.750  -0.3655   0.06704   0.06124  -0.0189   1.0000   0.2519
  -4.500  -0.3577   0.06424   0.05843  -0.0192   1.0000   0.2763
  -4.250  -0.3516   0.06111   0.05536  -0.0166   1.0000   0.3051
  -4.000  -0.3464   0.05834   0.05264  -0.0142   1.0000   0.3453
  -3.750  -0.3436   0.05517   0.04957  -0.0096   1.0000   0.3875
  -3.500  -0.3415   0.05235   0.04683  -0.0051   1.0000   0.4405
  -3.250  -0.3380   0.04905   0.04364   0.0000   1.0000   0.4829
  -3.000  -0.3306   0.04583   0.04050   0.0042   1.0000   0.5182
  -2.750  -0.1544   0.03723   0.02903  -0.0403   1.0000   0.1440
  -2.500  -0.1244   0.03441   0.02565  -0.0410   1.0000   0.1467
  -2.250  -0.0927   0.03161   0.02226  -0.0415   1.0000   0.1478
  -2.000  -0.0617   0.02908   0.01924  -0.0418   1.0000   0.1553
  -1.750  -0.0331   0.02730   0.01714  -0.0418   1.0000   0.1816
  -1.500  -0.0048   0.02578   0.01536  -0.0418   1.0000   0.2101
  -1.250   0.0241   0.02450   0.01378  -0.0415   1.0000   0.2296
  -1.000   0.0533   0.02357   0.01260  -0.0414   1.0000   0.2583
  -0.750   0.0829   0.02260   0.01160  -0.0413   1.0000   0.2905
  -0.500   0.1124   0.02128   0.01070  -0.0414   1.0000   0.3791
  -0.250   0.1328   0.01896   0.00979  -0.0389   1.0000   1.0000
   0.000   0.1559   0.01929   0.00964  -0.0383   1.0000   1.0000
   0.250   0.1782   0.01966   0.00966  -0.0379   1.0000   1.0000
   0.500   0.2001   0.02007   0.00984  -0.0375   1.0000   1.0000
   0.750   0.2216   0.02053   0.01012  -0.0371   1.0000   1.0000
   1.000   0.2427   0.02104   0.01050  -0.0368   1.0000   1.0000
   1.250   0.2632   0.02162   0.01099  -0.0366   1.0000   1.0000
   1.500   0.2831   0.02229   0.01159  -0.0365   1.0000   1.0000
   1.750   0.3021   0.02307   0.01232  -0.0365   1.0000   1.0000
   2.000   0.3200   0.02399   0.01323  -0.0366   1.0000   1.0000
   2.250   0.3837   0.02509   0.01435  -0.0453   0.9773   1.0000
   2.500   0.4685   0.02556   0.01493  -0.0564   0.9430   1.0000
   2.750   0.5396   0.02525   0.01479  -0.0637   0.9047   1.0000
   3.000   0.6083   0.02429   0.01408  -0.0691   0.8657   1.0000
   3.250   0.6656   0.02293   0.01300  -0.0712   0.8233   1.0000
   3.500   0.7084   0.02163   0.01185  -0.0703   0.7703   1.0000
   3.750   0.7425   0.02066   0.01082  -0.0677   0.7020   1.0000
   4.000   0.7719   0.02050   0.01033  -0.0651   0.6265   1.0000
   4.250   0.7972   0.02126   0.01064  -0.0631   0.5610   1.0000
   4.500   0.8222   0.02235   0.01145  -0.0618   0.5111   1.0000
   4.750   0.8466   0.02342   0.01233  -0.0607   0.4724   1.0000
   5.000   0.8653   0.02411   0.01281  -0.0587   0.4311   1.0000
   5.250   0.8872   0.02492   0.01364  -0.0574   0.4009   1.0000
   5.500   0.9086   0.02564   0.01433  -0.0561   0.3736   1.0000
   5.750   0.9277   0.02621   0.01485  -0.0545   0.3452   1.0000
   6.000   0.9473   0.02679   0.01542  -0.0530   0.3203   1.0000
   6.250   0.9703   0.02752   0.01631  -0.0521   0.3034   1.0000
   6.500   0.9922   0.02816   0.01711  -0.0510   0.2872   1.0000
   6.750   1.0061   0.02834   0.01745  -0.0487   0.2600   1.0000
   7.000   1.0259   0.02879   0.01811  -0.0473   0.2444   1.0000
   7.250   1.0426   0.02910   0.01867  -0.0454   0.2228   1.0000
   7.500   1.0594   0.02950   0.01927  -0.0435   0.1986   1.0000
   7.750   1.0758   0.03010   0.02003  -0.0416   0.1609   1.0000
   8.000   1.0927   0.03141   0.02123  -0.0398   0.1017   1.0000
   8.250   1.1066   0.03347   0.02302  -0.0379   0.0777   1.0000
   8.500   1.1189   0.03562   0.02510  -0.0358   0.0691   1.0000
   8.750   1.1304   0.03771   0.02733  -0.0336   0.0639   1.0000
   9.000   1.1389   0.04003   0.02985  -0.0313   0.0609   1.0000
   9.250   1.1496   0.04239   0.03237  -0.0289   0.0598   1.0000
   9.500   1.1643   0.04488   0.03512  -0.0268   0.0592   1.0000
   9.750   1.1819   0.04777   0.03831  -0.0251   0.0589   1.0000
  10.000   1.1989   0.05123   0.04213  -0.0236   0.0590   1.0000
  10.250   1.2110   0.05517   0.04645  -0.0219   0.0594   1.0000
  10.500   1.2170   0.05941   0.05106  -0.0201   0.0599   1.0000
  10.750   1.2158   0.06363   0.05572  -0.0180   0.0604   1.0000
  11.000   1.2004   0.06737   0.05991  -0.0150   0.0611   1.0000
  11.250   1.1788   0.07172   0.06464  -0.0129   0.0617   1.0000
  11.500   1.1531   0.07681   0.07006  -0.0126   0.0622   1.0000
  11.750   1.1242   0.08294   0.07646  -0.0144   0.0627   1.0000
  12.000   1.0912   0.09081   0.08454  -0.0190   0.0631   1.0000
  12.250   1.0509   0.10214   0.09602  -0.0277   0.0638   1.0000
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