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GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 533 AIRFOIL (goe533-il)
Reynolds number: 200,000
Max Cl/Cd: 73.76 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe533-il-200000.txt
Download as CSV file: xf-goe533-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 533 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2598   0.10463   0.10106  -0.0401   1.0000   0.0612
  -9.750  -0.2647   0.10166   0.09815  -0.0417   1.0000   0.0635
  -9.500  -0.3036   0.09786   0.09449  -0.0484   1.0000   0.0648
  -9.250  -0.2898   0.09443   0.09109  -0.0453   1.0000   0.0656
  -9.000  -0.2794   0.09258   0.08929  -0.0427   1.0000   0.0664
  -8.750  -0.2773   0.09096   0.08774  -0.0405   1.0000   0.0673
  -8.000  -0.2485   0.07591   0.07279  -0.0624   0.9728   0.0763
  -7.750  -0.2148   0.07369   0.07055  -0.0631   0.9645   0.0784
  -7.500  -0.2109   0.05878   0.05520  -0.0975   0.9307   0.0869
  -7.250  -0.1734   0.05638   0.05299  -0.0962   0.9205   0.0884
  -7.000  -0.1424   0.05443   0.05103  -0.0972   0.9009   0.0906
  -6.750  -0.1424   0.04779   0.04362  -0.1084   0.8680   0.1003
  -6.500  -0.1195   0.04492   0.04086  -0.1078   0.8482   0.1020
  -6.250  -0.0986   0.04338   0.03927  -0.1071   0.8291   0.1048
  -6.000  -0.0881   0.04022   0.03550  -0.1098   0.8110   0.1157
  -5.750  -0.0672   0.03805   0.03338  -0.1093   0.7969   0.1181
  -5.500  -0.0464   0.03634   0.03152  -0.1092   0.7844   0.1225
  -5.000  -0.0018   0.02295   0.01562  -0.1100   0.7645   0.0658
  -4.750   0.0244   0.02186   0.01423  -0.1095   0.7543   0.0653
  -4.500   0.0510   0.02101   0.01314  -0.1090   0.7444   0.0648
  -4.250   0.0774   0.01977   0.01169  -0.1086   0.7357   0.0646
  -4.000   0.1039   0.01886   0.01062  -0.1082   0.7265   0.0648
  -3.750   0.1306   0.01794   0.00954  -0.1078   0.7184   0.0652
  -3.500   0.1566   0.01702   0.00861  -0.1074   0.7099   0.0665
  -3.250   0.1832   0.01651   0.00807  -0.1070   0.7020   0.0686
  -3.000   0.2098   0.01606   0.00760  -0.1066   0.6942   0.0704
  -2.750   0.2365   0.01563   0.00711  -0.1061   0.6864   0.0721
  -2.500   0.2633   0.01530   0.00671  -0.1057   0.6792   0.0740
  -2.250   0.2895   0.01485   0.00629  -0.1053   0.6713   0.0770
  -2.000   0.3169   0.01464   0.00602  -0.1051   0.6646   0.0821
  -1.750   0.3433   0.01437   0.00579  -0.1047   0.6564   0.0900
  -1.500   0.3707   0.01409   0.00550  -0.1045   0.6494   0.1070
  -1.250   0.3930   0.01266   0.00541  -0.1043   0.6426   0.4625
  -1.000   0.4178   0.01255   0.00554  -0.1033   0.6350   0.5637
  -0.750   0.4439   0.01266   0.00568  -0.1025   0.6284   0.6172
  -0.500   0.4693   0.01273   0.00580  -0.1017   0.6200   0.6528
  -0.250   0.4953   0.01284   0.00587  -0.1009   0.6133   0.6879
   0.000   0.5197   0.01290   0.00601  -0.0998   0.6056   0.7214
   0.250   0.5437   0.01289   0.00605  -0.0985   0.5984   0.7556
   0.500   0.5678   0.01288   0.00607  -0.0973   0.5916   0.7873
   0.750   0.5916   0.01278   0.00605  -0.0962   0.5834   0.8126
   1.000   0.6168   0.01272   0.00597  -0.0952   0.5770   0.8429
   1.250   0.6418   0.01255   0.00597  -0.0942   0.5684   0.8910
   1.500   0.6878   0.01251   0.00585  -0.0978   0.5609   1.0000
   1.750   0.7163   0.01265   0.00593  -0.0983   0.5523   1.0000
   2.000   0.7451   0.01276   0.00589  -0.0985   0.5446   1.0000
   2.250   0.7724   0.01290   0.00597  -0.0985   0.5358   1.0000
   2.500   0.8001   0.01300   0.00594  -0.0984   0.5278   1.0000
   2.750   0.8269   0.01315   0.00604  -0.0982   0.5192   1.0000
   3.000   0.8542   0.01329   0.00609  -0.0981   0.5119   1.0000
   3.250   0.8810   0.01348   0.00624  -0.0979   0.5043   1.0000
   3.500   0.9077   0.01363   0.00633  -0.0977   0.4967   1.0000
   3.750   0.9346   0.01384   0.00647  -0.0975   0.4898   1.0000
   4.000   0.9607   0.01403   0.00664  -0.0971   0.4820   1.0000
   4.250   0.9880   0.01427   0.00676  -0.0970   0.4759   1.0000
   4.500   1.0134   0.01448   0.00703  -0.0966   0.4683   1.0000
   4.750   1.0400   0.01470   0.00717  -0.0964   0.4618   1.0000
   5.000   1.0654   0.01495   0.00743  -0.0959   0.4544   1.0000
   5.250   1.0911   0.01517   0.00762  -0.0956   0.4473   1.0000
   5.500   1.1170   0.01546   0.00787  -0.0953   0.4408   1.0000
   5.750   1.1420   0.01572   0.00816  -0.0948   0.4340   1.0000
   6.000   1.1685   0.01602   0.00840  -0.0946   0.4285   1.0000
   6.250   1.1929   0.01633   0.00878  -0.0941   0.4222   1.0000
   6.500   1.2179   0.01662   0.00908  -0.0936   0.4161   1.0000
   6.750   1.2444   0.01698   0.00937  -0.0935   0.4107   1.0000
   7.000   1.2672   0.01727   0.00979  -0.0927   0.4040   1.0000
   7.250   1.2917   0.01755   0.01004  -0.0922   0.3972   1.0000
   7.500   1.3144   0.01787   0.01042  -0.0914   0.3898   1.0000
   7.750   1.3372   0.01813   0.01070  -0.0906   0.3822   1.0000
   8.000   1.3598   0.01847   0.01106  -0.0898   0.3748   1.0000
   8.250   1.3811   0.01875   0.01140  -0.0888   0.3670   1.0000
   8.500   1.4031   0.01912   0.01177  -0.0880   0.3596   1.0000
   8.750   1.4231   0.01944   0.01218  -0.0868   0.3517   1.0000
   9.000   1.4443   0.01983   0.01257  -0.0858   0.3444   1.0000
   9.250   1.4622   0.02018   0.01303  -0.0843   0.3357   1.0000
   9.500   1.4806   0.02059   0.01345  -0.0830   0.3274   1.0000
   9.750   1.4968   0.02099   0.01391  -0.0813   0.3185   1.0000
  10.000   1.5123   0.02145   0.01443  -0.0795   0.3097   1.0000
  10.250   1.5263   0.02193   0.01493  -0.0775   0.3009   1.0000
  10.500   1.5374   0.02244   0.01555  -0.0750   0.2924   1.0000
  10.750   1.5479   0.02302   0.01611  -0.0725   0.2847   1.0000
  11.000   1.5563   0.02365   0.01686  -0.0699   0.2758   1.0000
  11.250   1.5644   0.02439   0.01757  -0.0673   0.2682   1.0000
  11.500   1.5722   0.02517   0.01849  -0.0650   0.2598   1.0000
  11.750   1.5784   0.02610   0.01941  -0.0626   0.2524   1.0000
  12.000   1.5844   0.02709   0.02053  -0.0604   0.2439   1.0000
  12.250   1.5883   0.02828   0.02175  -0.0582   0.2361   1.0000
  12.500   1.5900   0.02968   0.02321  -0.0561   0.2267   1.0000
  12.750   1.5907   0.03131   0.02489  -0.0543   0.2170   1.0000
  13.000   1.5891   0.03325   0.02684  -0.0526   0.2082   1.0000
  13.250   1.5873   0.03540   0.02904  -0.0513   0.1986   1.0000
  13.500   1.5849   0.03776   0.03146  -0.0502   0.1897   1.0000
  14.000   1.5744   0.04344   0.03721  -0.0487   0.1718   1.0000
  14.250   1.5675   0.04666   0.04049  -0.0482   0.1628   1.0000
  14.500   1.5566   0.05041   0.04423  -0.0480   0.1534   1.0000
  14.750   1.5483   0.05416   0.04808  -0.0481   0.1416   1.0000
  15.000   1.5383   0.05825   0.05224  -0.0484   0.1288   1.0000
  15.250   1.5264   0.06274   0.05675  -0.0490   0.1159   1.0000
  15.500   1.5127   0.06763   0.06162  -0.0498   0.1056   1.0000
  15.750   1.4985   0.07275   0.06673  -0.0509   0.0987   1.0000
  16.000   1.4839   0.07809   0.07206  -0.0521   0.0936   1.0000
  16.250   1.4727   0.08305   0.07706  -0.0534   0.0892   1.0000
  16.500   1.4621   0.08803   0.08208  -0.0547   0.0854   1.0000
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