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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 50,000
Max Cl/Cd: 33.56 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe529-il-50000-n5.txt
Download as CSV file: xf-goe529-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2601   0.10560   0.09960  -0.0326   1.0000   0.0966
  -7.750  -0.2746   0.10501   0.09916  -0.0300   1.0000   0.0980
  -7.500  -0.2911   0.10469   0.09900  -0.0276   0.9989   0.0991
  -7.250  -0.2766   0.10227   0.09659  -0.0398   0.9798   0.1015
  -7.000  -0.2547   0.09656   0.09086  -0.0403   0.9737   0.1044
  -6.750  -0.2318   0.09252   0.08678  -0.0436   0.9641   0.1108
  -6.500  -0.2128   0.09011   0.08430  -0.0576   0.9450   0.1165
  -6.250  -0.1915   0.08495   0.07915  -0.0593   0.9370   0.1182
  -6.000  -0.1717   0.08095   0.07512  -0.0603   0.9276   0.1215
  -5.500  -0.1244   0.07355   0.06759  -0.0707   0.9074   0.1363
  -5.000  -0.0613   0.06220   0.05568  -0.0870   0.8871   0.0841
  -4.750  -0.0362   0.05846   0.05176  -0.0903   0.8775   0.0823
  -4.500  -0.0094   0.05490   0.04795  -0.0942   0.8675   0.0834
  -4.250   0.0233   0.05104   0.04381  -0.0983   0.8607   0.0822
  -4.000   0.0477   0.04791   0.04040  -0.1003   0.8502   0.0806
  -3.750   0.0791   0.04455   0.03666  -0.1031   0.8426   0.0796
  -3.500   0.1080   0.04189   0.03360  -0.1050   0.8337   0.0818
  -3.250   0.1372   0.03938   0.03059  -0.1064   0.8250   0.0840
  -3.000   0.1693   0.03688   0.02760  -0.1079   0.8176   0.0843
  -2.750   0.1966   0.03496   0.02523  -0.1082   0.8085   0.0848
  -2.500   0.2297   0.03299   0.02272  -0.1092   0.8018   0.0858
  -2.250   0.2554   0.03166   0.02103  -0.1089   0.7926   0.0875
  -2.000   0.2866   0.03066   0.01991  -0.1096   0.7860   0.0929
  -1.750   0.3116   0.02990   0.01885  -0.1091   0.7767   0.0980
  -1.500   0.3456   0.02871   0.01718  -0.1096   0.7705   0.1018
  -1.250   0.3691   0.02813   0.01654  -0.1088   0.7612   0.1059
  -1.000   0.4033   0.02732   0.01545  -0.1093   0.7552   0.1136
  -0.750   0.4280   0.02704   0.01508  -0.1087   0.7459   0.1255
  -0.500   0.4605   0.02646   0.01432  -0.1090   0.7398   0.1465
  -0.250   0.4833   0.02626   0.01419  -0.1082   0.7303   0.1708
   0.000   0.5142   0.02567   0.01366  -0.1084   0.7244   0.2149
   0.250   0.5358   0.02541   0.01362  -0.1076   0.7148   0.2671
   0.500   0.5758   0.02320   0.01306  -0.1092   0.7093   1.0000
   0.750   0.5972   0.02365   0.01319  -0.1081   0.6996   1.0000
   1.000   0.6270   0.02376   0.01297  -0.1079   0.6931   1.0000
   1.250   0.6488   0.02420   0.01322  -0.1069   0.6835   1.0000
   1.500   0.6757   0.02444   0.01325  -0.1065   0.6763   1.0000
   1.750   0.6999   0.02479   0.01345  -0.1057   0.6676   1.0000
   2.000   0.7244   0.02515   0.01368  -0.1051   0.6594   1.0000
   2.250   0.7504   0.02544   0.01384  -0.1046   0.6515   1.0000
   2.500   0.7728   0.02591   0.01422  -0.1037   0.6427   1.0000
   2.750   0.8004   0.02614   0.01434  -0.1034   0.6354   1.0000
   3.000   0.8208   0.02672   0.01490  -0.1023   0.6259   1.0000
   3.250   0.8498   0.02688   0.01496  -0.1021   0.6191   1.0000
   3.500   0.8680   0.02758   0.01567  -0.1008   0.6090   1.0000
   3.750   0.8985   0.02766   0.01568  -0.1007   0.6027   1.0000
   4.000   0.9144   0.02847   0.01654  -0.0992   0.5920   1.0000
   4.250   0.9383   0.02889   0.01694  -0.0985   0.5840   1.0000
   4.500   0.9600   0.02940   0.01749  -0.0975   0.5751   1.0000
   4.750   0.9788   0.03007   0.01821  -0.0963   0.5658   1.0000
   5.000   1.0051   0.03032   0.01847  -0.0958   0.5584   1.0000
   5.250   1.0199   0.03121   0.01947  -0.0942   0.5484   1.0000
   5.500   1.0495   0.03127   0.01953  -0.0940   0.5421   1.0000
   5.750   1.0607   0.03237   0.02076  -0.0921   0.5317   1.0000
   6.000   1.0833   0.03282   0.02128  -0.0913   0.5243   1.0000
   6.500   1.1173   0.03438   0.02308  -0.0886   0.5073   1.0000
   6.750   1.1401   0.03481   0.02361  -0.0877   0.5000   1.0000
   7.000   1.1519   0.03594   0.02487  -0.0860   0.4913   1.0000
   7.250   1.1778   0.03621   0.02527  -0.0854   0.4848   1.0000
   7.500   1.1857   0.03758   0.02680  -0.0833   0.4758   1.0000
   7.750   1.2159   0.03751   0.02684  -0.0831   0.4694   1.0000
   8.000   1.2191   0.03913   0.02863  -0.0806   0.4597   1.0000
   8.250   1.2557   0.03862   0.02827  -0.0808   0.4537   1.0000
   8.500   1.2523   0.04061   0.03044  -0.0777   0.4433   1.0000
   8.750   1.2710   0.04114   0.03111  -0.0764   0.4350   1.0000
   9.000   1.2885   0.04166   0.03178  -0.0749   0.4262   1.0000
   9.250   1.2871   0.04340   0.03368  -0.0719   0.4168   1.0000
   9.500   1.3298   0.04233   0.03280  -0.0724   0.4087   1.0000
   9.750   1.3097   0.04524   0.03588  -0.0682   0.3983   1.0000
  10.000   1.3187   0.04635   0.03715  -0.0663   0.3890   1.0000
  10.250   1.3393   0.04662   0.03760  -0.0650   0.3802   1.0000
  10.500   1.3174   0.05042   0.04156  -0.0622   0.3703   1.0000
  10.750   1.3395   0.05043   0.04176  -0.0609   0.3614   1.0000
  11.000   1.3540   0.05052   0.04198  -0.0590   0.3486   1.0000
  11.250   1.3156   0.05694   0.04858  -0.0576   0.3400   1.0000
  11.500   1.3132   0.05921   0.05099  -0.0563   0.3278   1.0000
  11.750   1.3126   0.06110   0.05306  -0.0550   0.3138   1.0000
  12.750   1.2943   0.07198   0.06437  -0.0526   0.2513   1.0000
  13.000   1.2932   0.07424   0.06664  -0.0521   0.2308   1.0000
  13.250   1.2790   0.07915   0.07165  -0.0529   0.2131   1.0000
  13.500   1.2655   0.08414   0.07671  -0.0538   0.1922   1.0000
  13.750   1.2537   0.08911   0.08170  -0.0550   0.1694   1.0000
  14.000   1.2482   0.09272   0.08509  -0.0554   0.1403   1.0000
  14.250   1.2385   0.09726   0.08931  -0.0563   0.1189   1.0000
  14.500   1.2264   0.10276   0.09475  -0.0578   0.1013   1.0000
  14.750   1.2148   0.10850   0.10050  -0.0596   0.0824   1.0000
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