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GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 479 AIRFOIL (goe479-il)
Reynolds number: 100,000
Max Cl/Cd: 55.32 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe479-il-100000-n5.txt
Download as CSV file: xf-goe479-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 479 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3593   0.09245   0.08723  -0.0427   1.0000   0.0534
  -9.000  -0.3671   0.08938   0.08423  -0.0424   1.0000   0.0530
  -8.750  -0.3778   0.08645   0.08138  -0.0417   1.0000   0.0525
  -8.500  -0.3930   0.08367   0.07869  -0.0405   1.0000   0.0521
  -8.250  -0.4141   0.08117   0.07630  -0.0387   1.0000   0.0517
  -8.000  -0.4332   0.07783   0.07304  -0.0387   0.9988   0.0513
  -7.750  -0.4211   0.06910   0.06422  -0.0506   0.9884   0.0513
  -7.500  -0.4109   0.05990   0.05479  -0.0612   0.9778   0.0523
  -7.250  -0.4030   0.05040   0.04484  -0.0691   0.9673   0.0525
  -7.000  -0.3877   0.04291   0.03671  -0.0742   0.9593   0.0528
  -6.750  -0.3731   0.03798   0.03113  -0.0757   0.9493   0.0539
  -6.500  -0.3485   0.03402   0.02641  -0.0777   0.9429   0.0555
  -6.250  -0.3241   0.03226   0.02450  -0.0780   0.9346   0.0565
  -6.000  -0.2919   0.03033   0.02228  -0.0798   0.9299   0.0575
  -5.750  -0.2671   0.02881   0.02053  -0.0798   0.9214   0.0586
  -5.500  -0.2351   0.02732   0.01876  -0.0810   0.9157   0.0604
  -5.250  -0.2018   0.02590   0.01698  -0.0822   0.9105   0.0628
  -5.000  -0.1749   0.02471   0.01543  -0.0820   0.9016   0.0644
  -4.750  -0.1403   0.02346   0.01414  -0.0835   0.8969   0.0659
  -4.500  -0.1141   0.02264   0.01327  -0.0832   0.8875   0.0677
  -4.250  -0.0802   0.02181   0.01234  -0.0842   0.8814   0.0708
  -4.000  -0.0520   0.02110   0.01147  -0.0841   0.8718   0.0741
  -3.750  -0.0184   0.02021   0.01057  -0.0850   0.8644   0.0772
  -3.500   0.0084   0.01959   0.00994  -0.0846   0.8530   0.0806
  -3.250   0.0413   0.01895   0.00920  -0.0851   0.8448   0.0861
  -3.000   0.0680   0.01842   0.00872  -0.0848   0.8339   0.0921
  -2.750   0.0965   0.01796   0.00821  -0.0846   0.8244   0.0999
  -2.500   0.1263   0.01747   0.00776  -0.0848   0.8156   0.1117
  -2.250   0.1528   0.01708   0.00741  -0.0843   0.8051   0.1281
  -2.000   0.1838   0.01659   0.00703  -0.0847   0.7973   0.1564
  -1.750   0.2090   0.01627   0.00682  -0.0841   0.7861   0.1930
  -1.500   0.2377   0.01590   0.00660  -0.0841   0.7771   0.2419
  -1.250   0.2653   0.01554   0.00642  -0.0839   0.7674   0.3026
  -1.000   0.2923   0.01504   0.00630  -0.0837   0.7576   0.4042
  -0.750   0.3152   0.01415   0.00630  -0.0822   0.7490   0.6509
  -0.500   0.4104   0.01354   0.00620  -0.0944   0.7402   0.9826
  -0.250   0.4492   0.01356   0.00600  -0.0964   0.7310   1.0000
   0.000   0.4718   0.01368   0.00598  -0.0953   0.7196   1.0000
   0.250   0.4968   0.01377   0.00592  -0.0946   0.7098   1.0000
   0.500   0.5213   0.01388   0.00589  -0.0937   0.6996   1.0000
   0.750   0.5448   0.01403   0.00592  -0.0927   0.6890   1.0000
   1.000   0.5707   0.01414   0.00589  -0.0921   0.6799   1.0000
   1.250   0.5932   0.01431   0.00599  -0.0909   0.6686   1.0000
   1.500   0.6176   0.01447   0.00605  -0.0901   0.6584   1.0000
   1.750   0.6419   0.01463   0.00611  -0.0892   0.6481   1.0000
   2.000   0.6650   0.01482   0.00625  -0.0881   0.6370   1.0000
   2.250   0.6895   0.01498   0.00632  -0.0873   0.6264   1.0000
   2.500   0.7126   0.01516   0.00642  -0.0862   0.6140   1.0000
   2.750   0.7350   0.01534   0.00656  -0.0849   0.6005   1.0000
   3.000   0.7577   0.01552   0.00668  -0.0837   0.5873   1.0000
   3.250   0.7811   0.01571   0.00680  -0.0827   0.5753   1.0000
   3.500   0.8041   0.01591   0.00697  -0.0816   0.5633   1.0000
   3.750   0.8265   0.01613   0.00718  -0.0805   0.5510   1.0000
   4.000   0.8495   0.01635   0.00738  -0.0794   0.5395   1.0000
   4.250   0.8727   0.01657   0.00755  -0.0784   0.5282   1.0000
   4.500   0.8949   0.01681   0.00781  -0.0772   0.5160   1.0000
   4.750   0.9172   0.01707   0.00807  -0.0761   0.5041   1.0000
   5.000   0.9397   0.01733   0.00831  -0.0750   0.4926   1.0000
   5.250   0.9621   0.01760   0.00856  -0.0739   0.4812   1.0000
   5.500   0.9837   0.01791   0.00889  -0.0727   0.4690   1.0000
   5.750   1.0054   0.01823   0.00922  -0.0715   0.4572   1.0000
   6.000   1.0266   0.01856   0.00952  -0.0702   0.4448   1.0000
   6.250   1.0466   0.01892   0.00983  -0.0687   0.4301   1.0000
   6.500   1.0650   0.01929   0.01018  -0.0670   0.4135   1.0000
   6.750   1.0822   0.01969   0.01057  -0.0651   0.3952   1.0000
   7.000   1.0987   0.02010   0.01098  -0.0631   0.3764   1.0000
   7.250   1.1152   0.02053   0.01141  -0.0612   0.3589   1.0000
   7.500   1.1312   0.02099   0.01189  -0.0592   0.3415   1.0000
   7.750   1.1461   0.02148   0.01237  -0.0571   0.3236   1.0000
   8.000   1.1600   0.02202   0.01288  -0.0549   0.3054   1.0000
   8.250   1.1731   0.02260   0.01344  -0.0526   0.2887   1.0000
   8.500   1.1837   0.02322   0.01405  -0.0499   0.2722   1.0000
   8.750   1.1927   0.02393   0.01471  -0.0471   0.2555   1.0000
   9.000   1.2011   0.02472   0.01547  -0.0443   0.2380   1.0000
   9.250   1.2080   0.02564   0.01634  -0.0415   0.2180   1.0000
   9.500   1.2145   0.02663   0.01730  -0.0388   0.1989   1.0000
   9.750   1.2193   0.02779   0.01842  -0.0361   0.1781   1.0000
  10.000   1.2231   0.02909   0.01966  -0.0335   0.1521   1.0000
  10.250   1.2229   0.03073   0.02117  -0.0308   0.1240   1.0000
  10.500   1.2205   0.03265   0.02294  -0.0282   0.1008   1.0000
  10.750   1.2187   0.03467   0.02487  -0.0259   0.0877   1.0000
  11.000   1.2185   0.03667   0.02687  -0.0240   0.0806   1.0000
  11.250   1.2168   0.03891   0.02911  -0.0223   0.0758   1.0000
  11.500   1.2174   0.04105   0.03135  -0.0210   0.0725   1.0000
  11.750   1.2171   0.04337   0.03376  -0.0198   0.0698   1.0000
  12.000   1.2152   0.04596   0.03641  -0.0189   0.0676   1.0000
  12.250   1.2121   0.04874   0.03926  -0.0181   0.0660   1.0000
  12.500   1.2115   0.05140   0.04201  -0.0176   0.0644   1.0000
  12.750   1.2115   0.05405   0.04479  -0.0171   0.0630   1.0000
  13.000   1.2117   0.05674   0.04760  -0.0167   0.0619   1.0000
  13.250   1.2122   0.05946   0.05043  -0.0165   0.0608   1.0000
  13.500   1.2127   0.06221   0.05327  -0.0163   0.0595   1.0000
  13.750   1.2139   0.06492   0.05604  -0.0161   0.0584   1.0000
  14.000   1.2164   0.06748   0.05862  -0.0159   0.0573   1.0000
  14.250   1.2215   0.06971   0.06088  -0.0155   0.0561   1.0000
  14.500   1.2269   0.07208   0.06340  -0.0153   0.0550   1.0000
  14.750   1.2332   0.07434   0.06579  -0.0151   0.0540   1.0000
  15.000   1.2398   0.07659   0.06815  -0.0149   0.0530   1.0000
  15.250   1.2460   0.07893   0.07060  -0.0148   0.0519   1.0000
  15.500   1.2523   0.08126   0.07300  -0.0147   0.0508   1.0000
  15.750   1.2597   0.08343   0.07521  -0.0146   0.0496   1.0000
  16.000   1.2740   0.08469   0.07643  -0.0138   0.0484   1.0000
  16.250   1.2774   0.08763   0.07954  -0.0141   0.0477   1.0000
  16.500   1.2754   0.09138   0.08351  -0.0150   0.0470   1.0000
  16.750   1.2721   0.09537   0.08773  -0.0162   0.0463   1.0000
  17.000   1.2681   0.09954   0.09211  -0.0176   0.0455   1.0000
  17.250   1.2623   0.10407   0.09684  -0.0193   0.0448   1.0000
  17.500   1.2560   0.10878   0.10174  -0.0213   0.0441   1.0000
  17.750   1.2491   0.11369   0.10683  -0.0235   0.0434   1.0000
  18.000   1.2417   0.11877   0.11207  -0.0260   0.0429   1.0000
  18.250   1.2336   0.12406   0.11753  -0.0287   0.0424   1.0000
  18.500   1.2283   0.12888   0.12246  -0.0311   0.0418   1.0000
  18.750   1.2333   0.13164   0.12525  -0.0321   0.0409   1.0000
  19.000   1.2140   0.13955   0.13336  -0.0370   0.0407   1.0000
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