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GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 553 AIRFOIL (goe553-il)
Reynolds number: 500,000
Max Cl/Cd: 105.51 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe553-il-500000.txt
Download as CSV file: xf-goe553-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3046   0.13013   0.12765  -0.0311   1.0000   0.0284
 -12.250  -0.3212   0.12330   0.12083  -0.0370   1.0000   0.0300
 -12.000  -0.3166   0.11961   0.11716  -0.0372   1.0000   0.0302
 -11.750  -0.3056   0.11763   0.11519  -0.0366   1.0000   0.0305
 -11.500  -0.2965   0.11540   0.11297  -0.0364   1.0000   0.0308
 -11.250  -0.2897   0.11294   0.11053  -0.0367   1.0000   0.0312
 -11.000  -0.2848   0.11021   0.10783  -0.0372   1.0000   0.0316
 -10.750  -0.2308   0.09534   0.09321  -0.0453   1.0000   0.0349
 -10.500  -0.2241   0.09328   0.09118  -0.0439   1.0000   0.0352
 -10.250  -0.2083   0.09072   0.08862  -0.0448   0.9983   0.0356
 -10.000  -0.1916   0.08733   0.08523  -0.0473   0.9911   0.0361
  -9.750  -0.1773   0.08335   0.08125  -0.0505   0.9820   0.0369
  -9.500  -0.1656   0.07833   0.07622  -0.0549   0.9705   0.0383
  -9.000  -0.2624   0.08264   0.08047  -0.0494   0.9903   0.0374
  -8.750  -0.2935   0.06126   0.05907  -0.0769   0.9643   0.0406
  -8.500  -0.2578   0.06111   0.05892  -0.0783   0.9524   0.0410
  -8.250  -0.2186   0.05611   0.05385  -0.0898   0.9303   0.0417
  -8.000  -0.1991   0.04809   0.04551  -0.1045   0.8850   0.0427
  -7.750  -0.2362   0.03748   0.03382  -0.1104   0.8337   0.0471
  -7.500  -0.2178   0.03587   0.03213  -0.1098   0.7984   0.0475
  -7.250  -0.2006   0.03459   0.03069  -0.1091   0.7682   0.0481
  -7.000  -0.1826   0.03324   0.02918  -0.1087   0.7450   0.0488
  -6.750  -0.1644   0.03166   0.02738  -0.1084   0.7274   0.0501
  -6.500  -0.1515   0.02831   0.02336  -0.1084   0.7143   0.0549
  -6.250  -0.1370   0.02113   0.01496  -0.1071   0.7044   0.0404
  -6.000  -0.1123   0.01982   0.01349  -0.1067   0.6942   0.0400
  -5.750  -0.0876   0.01844   0.01191  -0.1063   0.6849   0.0399
  -5.500  -0.0619   0.01751   0.01078  -0.1060   0.6766   0.0400
  -5.250  -0.0357   0.01680   0.00990  -0.1056   0.6685   0.0402
  -5.000  -0.0102   0.01558   0.00853  -0.1052   0.6615   0.0407
  -4.750   0.0161   0.01472   0.00765  -0.1050   0.6545   0.0413
  -4.500   0.0426   0.01417   0.00702  -0.1046   0.6479   0.0418
  -4.250   0.0694   0.01367   0.00648  -0.1043   0.6419   0.0423
  -4.000   0.0964   0.01323   0.00601  -0.1040   0.6357   0.0428
  -3.750   0.1233   0.01287   0.00558  -0.1037   0.6299   0.0434
  -3.500   0.1504   0.01252   0.00520  -0.1034   0.6242   0.0441
  -3.250   0.1776   0.01219   0.00485  -0.1032   0.6183   0.0449
  -3.000   0.2050   0.01199   0.00457  -0.1029   0.6129   0.0459
  -2.750   0.2322   0.01172   0.00427  -0.1026   0.6076   0.0468
  -2.500   0.2591   0.01129   0.00385  -0.1024   0.6018   0.0482
  -2.250   0.2864   0.01107   0.00360  -0.1022   0.5959   0.0497
  -2.000   0.3140   0.01091   0.00340  -0.1020   0.5904   0.0514
  -1.750   0.3420   0.01074   0.00322  -0.1018   0.5846   0.0533
  -1.500   0.3696   0.01054   0.00299  -0.1016   0.5788   0.0566
  -1.250   0.3973   0.01044   0.00285  -0.1014   0.5732   0.0619
  -1.000   0.4249   0.01014   0.00273  -0.1013   0.5668   0.0961
  -0.750   0.4501   0.00926   0.00257  -0.1013   0.5605   0.3314
  -0.500   0.4762   0.00892   0.00265  -0.1011   0.5543   0.4862
  -0.250   0.5036   0.00885   0.00270  -0.1008   0.5472   0.5361
   0.000   0.5306   0.00889   0.00272  -0.1004   0.5399   0.5659
   0.250   0.5582   0.00886   0.00275  -0.1001   0.5314   0.5898
   0.500   0.5852   0.00892   0.00276  -0.0998   0.5232   0.6113
   0.750   0.6126   0.00891   0.00280  -0.0995   0.5144   0.6322
   1.000   0.6390   0.00895   0.00285  -0.0990   0.5065   0.6578
   1.250   0.6662   0.00896   0.00291  -0.0987   0.4977   0.6801
   1.500   0.6927   0.00902   0.00295  -0.0982   0.4893   0.6965
   1.750   0.7198   0.00904   0.00300  -0.0979   0.4805   0.7118
   2.000   0.7461   0.00910   0.00305  -0.0975   0.4723   0.7294
   2.250   0.7726   0.00913   0.00312  -0.0971   0.4631   0.7506
   2.500   0.7979   0.00915   0.00320  -0.0965   0.4543   0.7797
   2.750   0.8216   0.00908   0.00327  -0.0954   0.4455   0.8315
   3.000   0.8598   0.00897   0.00334  -0.0975   0.4365   1.0000
   3.250   0.8867   0.00914   0.00343  -0.0973   0.4283   1.0000
   3.500   0.9135   0.00932   0.00355  -0.0971   0.4210   1.0000
   3.750   0.9403   0.00948   0.00367  -0.0969   0.4138   1.0000
   4.000   0.9664   0.00969   0.00381  -0.0965   0.4072   1.0000
   4.250   0.9933   0.00984   0.00395  -0.0963   0.4004   1.0000
   4.500   1.0191   0.01005   0.00410  -0.0959   0.3938   1.0000
   4.750   1.0455   0.01022   0.00426  -0.0957   0.3878   1.0000
   5.000   1.0717   0.01041   0.00443  -0.0953   0.3814   1.0000
   5.250   1.0967   0.01066   0.00462  -0.0949   0.3754   1.0000
   5.500   1.1234   0.01080   0.00479  -0.0946   0.3703   1.0000
   5.750   1.1490   0.01100   0.00498  -0.0943   0.3648   1.0000
   6.000   1.1737   0.01127   0.00520  -0.0937   0.3595   1.0000
   6.250   1.1999   0.01143   0.00540  -0.0934   0.3547   1.0000
   6.500   1.2252   0.01163   0.00561  -0.0930   0.3493   1.0000
   6.750   1.2492   0.01191   0.00585  -0.0924   0.3438   1.0000
   7.000   1.2746   0.01208   0.00606  -0.0920   0.3374   1.0000
   7.250   1.2983   0.01233   0.00629  -0.0914   0.3301   1.0000
   7.500   1.3224   0.01256   0.00654  -0.0908   0.3234   1.0000
   7.750   1.3462   0.01280   0.00678  -0.0902   0.3161   1.0000
   8.000   1.3689   0.01309   0.00706  -0.0894   0.3097   1.0000
   8.250   1.3925   0.01332   0.00733  -0.0887   0.3020   1.0000
   8.500   1.4140   0.01364   0.00763  -0.0877   0.2938   1.0000
   8.750   1.4360   0.01393   0.00793  -0.0869   0.2841   1.0000
   9.000   1.4569   0.01425   0.00826  -0.0858   0.2743   1.0000
   9.250   1.4759   0.01466   0.00863  -0.0845   0.2636   1.0000
   9.500   1.4946   0.01505   0.00902  -0.0831   0.2518   1.0000
   9.750   1.5114   0.01548   0.00944  -0.0814   0.2398   1.0000
  10.000   1.5248   0.01599   0.00992  -0.0792   0.2276   1.0000
  10.250   1.5366   0.01657   0.01046  -0.0767   0.2166   1.0000
  10.750   1.5589   0.01785   0.01170  -0.0720   0.1984   1.0000
  11.000   1.5673   0.01865   0.01248  -0.0694   0.1902   1.0000
  11.250   1.5766   0.01945   0.01328  -0.0672   0.1829   1.0000
  11.500   1.5839   0.02039   0.01422  -0.0648   0.1765   1.0000
  11.750   1.5939   0.02125   0.01512  -0.0628   0.1708   1.0000
  12.000   1.5994   0.02240   0.01629  -0.0606   0.1656   1.0000
  12.250   1.6090   0.02339   0.01734  -0.0590   0.1607   1.0000
  12.500   1.6161   0.02461   0.01860  -0.0573   0.1548   1.0000
  12.750   1.6192   0.02617   0.02018  -0.0555   0.1492   1.0000
  13.000   1.6286   0.02740   0.02147  -0.0544   0.1412   1.0000
  13.250   1.6321   0.02913   0.02323  -0.0531   0.1316   1.0000
  13.750   1.6130   0.03536   0.02924  -0.0504   0.0883   1.0000
  14.000   1.6001   0.03912   0.03297  -0.0496   0.0792   1.0000
  14.250   1.5916   0.04258   0.03647  -0.0490   0.0743   1.0000
  14.500   1.5811   0.04637   0.04031  -0.0487   0.0705   1.0000
  14.750   1.5771   0.04954   0.04358  -0.0485   0.0678   1.0000
  15.000   1.5703   0.05314   0.04726  -0.0485   0.0651   1.0000
  15.250   1.5603   0.05724   0.05142  -0.0488   0.0628   1.0000
  15.500   1.5494   0.06160   0.05585  -0.0492   0.0607   1.0000
  15.750   1.5478   0.06493   0.05929  -0.0496   0.0588   1.0000
  16.000   1.5424   0.06881   0.06326  -0.0503   0.0569   1.0000
  16.250   1.5342   0.07319   0.06772  -0.0512   0.0550   1.0000
  16.500   1.5227   0.07818   0.07277  -0.0523   0.0532   1.0000
  16.750   1.5169   0.08244   0.07713  -0.0534   0.0517   1.0000
  17.000   1.5149   0.08621   0.08100  -0.0544   0.0498   1.0000
  17.250   1.5085   0.09071   0.08557  -0.0557   0.0481   1.0000
  17.500   1.4989   0.09578   0.09070  -0.0574   0.0464   1.0000
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