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GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 553 AIRFOIL (goe553-il)
Reynolds number: 200,000
Max Cl/Cd: 73.04 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe553-il-200000.txt
Download as CSV file: xf-goe553-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 553 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2633   0.09342   0.09006  -0.0402   1.0000   0.0671
  -8.750  -0.2728   0.09100   0.08774  -0.0403   1.0000   0.0695
  -8.500  -0.3174   0.08326   0.08017  -0.0566   0.9883   0.0718
  -8.250  -0.2766   0.08245   0.07934  -0.0487   0.9902   0.0731
  -8.000  -0.2436   0.07949   0.07636  -0.0517   0.9832   0.0753
  -7.750  -0.2441   0.06395   0.06061  -0.0866   0.9506   0.0830
  -7.500  -0.2069   0.06323   0.06005  -0.0821   0.9434   0.0842
  -7.250  -0.1726   0.06170   0.05851  -0.0823   0.9298   0.0865
  -7.000  -0.1631   0.05034   0.04655  -0.1042   0.8974   0.0960
  -6.750  -0.1327   0.04837   0.04466  -0.1041   0.8775   0.0979
  -6.500  -0.1030   0.03377   0.02986  -0.0984   0.8099   0.1070
  -6.250  -0.0989   0.02886   0.02471  -0.1003   0.7966   0.1110
  -6.000  -0.0800   0.02707   0.02289  -0.0996   0.7847   0.1135
  -5.750  -0.0637   0.02480   0.02045  -0.1001   0.7725   0.1187
  -5.500  -0.0489   0.02761   0.02104  -0.1101   0.7872   0.0714
  -5.250  -0.0262   0.02504   0.01829  -0.1098   0.7747   0.0701
  -5.000  -0.0017   0.02307   0.01602  -0.1095   0.7639   0.0684
  -4.750   0.0237   0.02130   0.01387  -0.1090   0.7535   0.0665
  -4.500   0.0498   0.01996   0.01223  -0.1084   0.7434   0.0656
  -4.250   0.0766   0.01897   0.01097  -0.1079   0.7344   0.0656
  -4.000   0.1029   0.01824   0.01012  -0.1075   0.7247   0.0666
  -3.750   0.1300   0.01765   0.00937  -0.1070   0.7165   0.0681
  -3.500   0.1564   0.01704   0.00868  -0.1065   0.7074   0.0692
  -3.250   0.1834   0.01650   0.00801  -0.1061   0.6997   0.0701
  -3.000   0.2099   0.01605   0.00750  -0.1056   0.6913   0.0713
  -2.750   0.2360   0.01545   0.00689  -0.1051   0.6837   0.0730
  -2.500   0.2624   0.01510   0.00656  -0.1047   0.6760   0.0761
  -2.250   0.2891   0.01485   0.00629  -0.1043   0.6681   0.0805
  -2.000   0.3160   0.01455   0.00596  -0.1040   0.6611   0.0854
  -1.750   0.3427   0.01433   0.00573  -0.1036   0.6528   0.0935
  -1.500   0.3701   0.01399   0.00541  -0.1034   0.6462   0.1168
  -1.250   0.3909   0.01259   0.00546  -0.1028   0.6386   0.4971
  -1.000   0.4167   0.01263   0.00558  -0.1020   0.6312   0.5712
  -0.750   0.4428   0.01275   0.00569  -0.1013   0.6238   0.6116
  -0.500   0.4683   0.01280   0.00578  -0.1004   0.6157   0.6451
  -0.250   0.4944   0.01291   0.00585  -0.0996   0.6092   0.6733
   0.000   0.5188   0.01293   0.00597  -0.0985   0.6008   0.7042
   0.250   0.5434   0.01297   0.00601  -0.0974   0.5941   0.7380
   0.500   0.5675   0.01297   0.00609  -0.0962   0.5861   0.7656
   0.750   0.5929   0.01293   0.00604  -0.0954   0.5784   0.7871
   1.000   0.6180   0.01290   0.00604  -0.0946   0.5709   0.8098
   1.250   0.6427   0.01280   0.00601  -0.0937   0.5628   0.8381
   1.500   0.6702   0.01269   0.00594  -0.0932   0.5562   0.8845
   1.750   0.7146   0.01260   0.00590  -0.0966   0.5460   1.0000
   2.000   0.7441   0.01275   0.00588  -0.0971   0.5383   1.0000
   2.250   0.7716   0.01284   0.00591  -0.0971   0.5288   1.0000
   2.500   0.7995   0.01299   0.00592  -0.0971   0.5210   1.0000
   2.750   0.8263   0.01312   0.00600  -0.0969   0.5121   1.0000
   3.000   0.8538   0.01330   0.00605  -0.0968   0.5052   1.0000
   3.250   0.8801   0.01345   0.00620  -0.0965   0.4966   1.0000
   3.500   0.9076   0.01365   0.00625  -0.0964   0.4901   1.0000
   3.750   0.9332   0.01383   0.00647  -0.0960   0.4817   1.0000
   4.000   0.9602   0.01404   0.00656  -0.0958   0.4750   1.0000
   4.250   0.9860   0.01427   0.00680  -0.0954   0.4676   1.0000
   4.500   1.0123   0.01448   0.00697  -0.0951   0.4606   1.0000
   4.750   1.0383   0.01474   0.00718  -0.0948   0.4537   1.0000
   5.000   1.0638   0.01496   0.00739  -0.0943   0.4461   1.0000
   5.250   1.0901   0.01524   0.00759  -0.0941   0.4397   1.0000
   5.500   1.1147   0.01548   0.00789  -0.0935   0.4324   1.0000
   5.750   1.1408   0.01576   0.00810  -0.0932   0.4264   1.0000
   6.000   1.1659   0.01608   0.00846  -0.0928   0.4203   1.0000
   6.250   1.1907   0.01636   0.00876  -0.0923   0.4140   1.0000
   6.500   1.2171   0.01671   0.00902  -0.0921   0.4086   1.0000
   6.750   1.2405   0.01702   0.00945  -0.0914   0.4022   1.0000
   7.000   1.2650   0.01732   0.00976  -0.0909   0.3961   1.0000
   7.250   1.2904   0.01770   0.01010  -0.0906   0.3904   1.0000
   7.500   1.3128   0.01801   0.01053  -0.0898   0.3837   1.0000
   7.750   1.3371   0.01834   0.01083  -0.0892   0.3776   1.0000
   8.000   1.3594   0.01870   0.01127  -0.0884   0.3707   1.0000
   8.250   1.3811   0.01898   0.01158  -0.0874   0.3628   1.0000
   8.500   1.4019   0.01932   0.01196  -0.0864   0.3545   1.0000
   8.750   1.4221   0.01962   0.01227  -0.0852   0.3460   1.0000
   9.000   1.4415   0.02000   0.01272  -0.0839   0.3378   1.0000
   9.250   1.4606   0.02036   0.01309  -0.0826   0.3294   1.0000
   9.500   1.4774   0.02077   0.01359  -0.0810   0.3203   1.0000
   9.750   1.4950   0.02120   0.01397  -0.0795   0.3117   1.0000
  10.000   1.5085   0.02164   0.01456  -0.0774   0.3021   1.0000
  10.250   1.5231   0.02217   0.01506  -0.0755   0.2938   1.0000
  10.500   1.5333   0.02267   0.01567  -0.0729   0.2850   1.0000
  10.750   1.5438   0.02328   0.01628  -0.0704   0.2773   1.0000
  11.000   1.5524   0.02391   0.01700  -0.0678   0.2691   1.0000
  11.250   1.5609   0.02465   0.01776  -0.0653   0.2615   1.0000
  11.500   1.5688   0.02544   0.01863  -0.0630   0.2540   1.0000
  11.750   1.5765   0.02634   0.01955  -0.0608   0.2475   1.0000
  12.000   1.5832   0.02731   0.02063  -0.0587   0.2402   1.0000
  12.250   1.5889   0.02844   0.02175  -0.0566   0.2341   1.0000
  12.500   1.5939   0.02966   0.02310  -0.0548   0.2266   1.0000
  12.750   1.5952   0.03116   0.02460  -0.0528   0.2193   1.0000
  13.000   1.5975   0.03277   0.02632  -0.0513   0.2113   1.0000
  13.250   1.5973   0.03466   0.02824  -0.0498   0.2041   1.0000
  13.500   1.5966   0.03677   0.03043  -0.0487   0.1960   1.0000
  13.750   1.5943   0.03914   0.03286  -0.0477   0.1884   1.0000
  14.000   1.5904   0.04180   0.03555  -0.0469   0.1806   1.0000
  14.250   1.5859   0.04466   0.03850  -0.0464   0.1724   1.0000
  14.500   1.5768   0.04807   0.04188  -0.0460   0.1642   1.0000
  14.750   1.5703   0.05147   0.04543  -0.0459   0.1547   1.0000
  15.000   1.5598   0.05542   0.04944  -0.0461   0.1447   1.0000
  15.250   1.5475   0.05980   0.05388  -0.0466   0.1335   1.0000
  15.500   1.5349   0.06446   0.05860  -0.0474   0.1202   1.0000
  15.750   1.5200   0.06959   0.06372  -0.0485   0.1078   1.0000
  16.000   1.5034   0.07514   0.06925  -0.0498   0.0994   1.0000
  16.250   1.4877   0.08071   0.07481  -0.0513   0.0931   1.0000
  16.500   1.4729   0.08627   0.08038  -0.0528   0.0885   1.0000
  16.750   1.4615   0.09144   0.08559  -0.0543   0.0842   1.0000
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