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GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 574 AIRFOIL (goe574-il)
Reynolds number: 200,000
Max Cl/Cd: 74.46 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe574-il-200000.txt
Download as CSV file: xf-goe574-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 574 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3607   0.09956   0.09657  -0.0318   1.0000   0.0299
  -7.500  -0.3677   0.09718   0.09425  -0.0314   1.0000   0.0299
  -7.250  -0.3761   0.09494   0.09208  -0.0305   1.0000   0.0299
  -7.000  -0.3705   0.08798   0.08516  -0.0313   0.9974   0.0308
  -6.750  -0.3490   0.08378   0.08095  -0.0332   0.9937   0.0319
  -6.500  -0.3228   0.07949   0.07663  -0.0384   0.9876   0.0341
  -6.250  -0.2941   0.07433   0.07139  -0.0465   0.9793   0.0366
  -6.000  -0.2574   0.06835   0.06527  -0.0583   0.9687   0.0398
  -5.750  -0.2187   0.06321   0.05980  -0.0678   0.9569   0.0409
  -5.500  -0.2048   0.05635   0.05298  -0.0703   0.9506   0.0424
  -5.250  -0.1856   0.05333   0.04996  -0.0710   0.9397   0.0443
  -5.000  -0.1614   0.04984   0.04635  -0.0733   0.9286   0.0477
  -4.750  -0.0850   0.02795   0.02444  -0.0807   0.8994   0.0589
  -4.500  -0.0583   0.02372   0.01972  -0.0836   0.8893   0.0684
  -4.250  -0.0258   0.02070   0.01670  -0.0862   0.8818   0.0738
  -4.000  -0.0489   0.03525   0.03089  -0.0818   0.8901   0.0734
  -3.750  -0.0133   0.03195   0.02726  -0.0844   0.8818   0.0850
  -3.500   0.0247   0.02924   0.02427  -0.0873   0.8714   0.0993
  -3.250   0.0677   0.02715   0.02194  -0.0912   0.8591   0.1188
  -3.000  -0.0657   0.08234   0.07933  -0.0923   0.9170   0.0903
  -2.750   0.1655   0.01848   0.01137  -0.0962   0.8336   0.0645
  -2.500   0.2105   0.01651   0.00894  -0.0994   0.8167   0.0619
  -2.250   0.2507   0.01537   0.00745  -0.1017   0.7986   0.0616
  -2.000   0.2812   0.01486   0.00671  -0.1020   0.7788   0.0646
  -1.750   0.3093   0.01426   0.00594  -0.1017   0.7593   0.0650
  -1.500   0.3358   0.01382   0.00534  -0.1012   0.7404   0.0658
  -1.250   0.3580   0.01344   0.00487  -0.0998   0.7209   0.0672
  -1.000   0.3792   0.01305   0.00439  -0.0982   0.7020   0.0701
  -0.750   0.4015   0.01290   0.00413  -0.0969   0.6842   0.0757
  -0.500   0.5760   0.01076   0.00419  -0.1295   0.6566   1.0000
  -0.250   0.5978   0.01092   0.00412  -0.1282   0.6407   1.0000
   0.000   0.6199   0.01109   0.00409  -0.1270   0.6264   1.0000
   0.250   0.6422   0.01126   0.00408  -0.1258   0.6134   1.0000
   0.500   0.6647   0.01143   0.00411  -0.1248   0.6018   1.0000
   0.750   0.6879   0.01161   0.00414  -0.1239   0.5918   1.0000
   1.000   0.7114   0.01179   0.00419  -0.1231   0.5830   1.0000
   1.250   0.7346   0.01197   0.00430  -0.1222   0.5747   1.0000
   1.500   0.7592   0.01217   0.00438  -0.1216   0.5680   1.0000
   1.750   0.7826   0.01235   0.00453  -0.1208   0.5613   1.0000
   2.000   0.8068   0.01255   0.00465  -0.1201   0.5553   1.0000
   2.250   0.8311   0.01276   0.00484  -0.1196   0.5498   1.0000
   2.500   0.8545   0.01295   0.00502  -0.1187   0.5441   1.0000
   2.750   0.8797   0.01318   0.00520  -0.1183   0.5397   1.0000
   3.000   0.9039   0.01342   0.00544  -0.1177   0.5355   1.0000
   3.250   0.9274   0.01364   0.00572  -0.1170   0.5310   1.0000
   3.500   0.9521   0.01388   0.00595  -0.1165   0.5268   1.0000
   3.750   0.9781   0.01417   0.00622  -0.1163   0.5232   1.0000
   4.000   0.9990   0.01438   0.00653  -0.1150   0.5182   1.0000
   4.250   1.0223   0.01460   0.00679  -0.1141   0.5130   1.0000
   4.500   1.0436   0.01481   0.00702  -0.1128   0.5061   1.0000
   4.750   1.0588   0.01483   0.00701  -0.1101   0.4923   1.0000
   5.000   1.0764   0.01493   0.00706  -0.1079   0.4805   1.0000
   5.250   1.0925   0.01503   0.00728  -0.1055   0.4715   1.0000
   5.500   1.1066   0.01510   0.00739  -0.1025   0.4584   1.0000
   5.750   1.1177   0.01514   0.00744  -0.0989   0.4424   1.0000
   6.000   1.1292   0.01521   0.00754  -0.0954   0.4267   1.0000
   6.250   1.1362   0.01526   0.00761  -0.0910   0.4038   1.0000
   6.500   1.1381   0.01537   0.00766  -0.0854   0.3656   1.0000
   6.750   1.1266   0.01621   0.00793  -0.0776   0.2554   1.0000
   7.000   1.1069   0.01806   0.00909  -0.0690   0.1529   1.0000
   7.250   1.0841   0.02007   0.01051  -0.0602   0.0479   1.0000
   7.500   1.0877   0.02098   0.01144  -0.0558   0.0379   1.0000
   7.750   1.0959   0.02172   0.01233  -0.0523   0.0349   1.0000
   8.000   1.1019   0.02259   0.01335  -0.0486   0.0326   1.0000
   8.250   1.1057   0.02360   0.01450  -0.0448   0.0311   1.0000
   8.500   1.1045   0.02490   0.01595  -0.0405   0.0297   1.0000
   8.750   1.1006   0.02641   0.01760  -0.0361   0.0289   1.0000
   9.000   1.0909   0.02840   0.01970  -0.0316   0.0281   1.0000
   9.250   1.0940   0.02978   0.02119  -0.0289   0.0269   1.0000
   9.500   1.0916   0.03168   0.02319  -0.0261   0.0268   1.0000
   9.750   1.0900   0.03371   0.02531  -0.0235   0.0265   1.0000
  10.000   1.0899   0.03579   0.02750  -0.0213   0.0262   1.0000
  10.250   1.0925   0.03775   0.02953  -0.0192   0.0260   1.0000
  10.500   1.0999   0.03946   0.03127  -0.0171   0.0259   1.0000
  10.750   1.1148   0.04087   0.03271  -0.0151   0.0260   1.0000
  11.000   1.1430   0.04206   0.03393  -0.0135   0.0263   1.0000
  11.250   1.1686   0.04352   0.03550  -0.0125   0.0254   1.0000
  17.500   0.7069   0.17201   0.16878  -0.0402   0.0666   1.0000
  17.750   0.7141   0.17402   0.17082  -0.0406   0.0635   1.0000
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