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GOE 29B AIRFOIL (goe29b-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 29B AIRFOIL (goe29b-il)
Reynolds number: 500,000
Max Cl/Cd: 99.4 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe29b-il-500000.txt
Download as CSV file: xf-goe29b-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 29B 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1919   0.09780   0.09555  -0.0258   0.9095   0.0287
  -8.000  -0.1863   0.09526   0.09292  -0.0277   0.8870   0.0298
  -7.750  -0.1846   0.09296   0.09054  -0.0325   0.8651   0.0300
  -7.500  -0.1774   0.08982   0.08734  -0.0348   0.8471   0.0301
  -7.250  -0.1663   0.08668   0.08414  -0.0333   0.8300   0.0303
  -7.000  -0.1546   0.08405   0.08144  -0.0337   0.8106   0.0304
  -6.750  -0.1417   0.08154   0.07885  -0.0350   0.7895   0.0307
  -6.500  -0.1274   0.07903   0.07625  -0.0371   0.7674   0.0310
  -6.250  -0.1116   0.07645   0.07357  -0.0397   0.7456   0.0315
  -6.000  -0.0941   0.07374   0.07076  -0.0429   0.7250   0.0322
  -5.750  -0.0737   0.07079   0.06771  -0.0471   0.7068   0.0334
  -5.500  -0.0302   0.06548   0.06220  -0.0639   0.6921   0.0344
  -5.250  -0.0171   0.06283   0.05949  -0.0626   0.6779   0.0346
  -5.000   0.0006   0.06042   0.05701  -0.0633   0.6651   0.0348
  -4.750   0.0220   0.05807   0.05459  -0.0652   0.6537   0.0352
  -4.500   0.0461   0.05570   0.05212  -0.0679   0.6433   0.0357
  -4.250   0.0730   0.05316   0.04952  -0.0713   0.6348   0.0365
  -4.000   0.1328   0.04872   0.04474  -0.0845   0.6266   0.0390
  -3.750   0.1527   0.04562   0.04161  -0.0855   0.6188   0.0393
  -3.500   0.1740   0.04359   0.03955  -0.0860   0.6104   0.0396
  -3.250   0.1989   0.04170   0.03759  -0.0873   0.6026   0.0400
  -3.000   0.2268   0.03978   0.03560  -0.0891   0.5942   0.0408
  -2.750   0.2571   0.03777   0.03347  -0.0913   0.5862   0.0420
  -2.500   0.3074   0.03388   0.02919  -0.0972   0.5780   0.0445
  -2.250   0.3308   0.03215   0.02742  -0.0978   0.5699   0.0449
  -2.000   0.3567   0.03079   0.02603  -0.0984   0.5611   0.0455
  -1.750   0.3849   0.02944   0.02457  -0.0993   0.5527   0.0465
  -1.500   0.4287   0.02747   0.02217  -0.1014   0.5440   0.0503
  -1.250   0.4558   0.02492   0.01950  -0.1026   0.5352   0.0508
  -1.000   0.4827   0.02378   0.01833  -0.1031   0.5243   0.0514
  -0.750   0.5107   0.02282   0.01727  -0.1036   0.5145   0.0523
  -0.500   0.5402   0.02179   0.01611  -0.1040   0.5054   0.0541
  -0.250   0.5753   0.01981   0.01371  -0.1047   0.4979   0.0579
   0.000   0.6094   0.01647   0.00982  -0.1052   0.4904   0.0502
   0.250   0.6393   0.01494   0.00795  -0.1054   0.4826   0.0504
   0.500   0.6670   0.01469   0.00775  -0.1056   0.4742   0.0519
   0.750   0.6951   0.01451   0.00748  -0.1056   0.4668   0.0539
   1.000   0.7246   0.01364   0.00640  -0.1056   0.4600   0.0553
   1.250   0.7534   0.01324   0.00573  -0.1054   0.4536   0.0572
   1.500   0.7816   0.01283   0.00534  -0.1054   0.4476   0.0594
   1.750   0.8096   0.01276   0.00525  -0.1054   0.4411   0.0622
   2.000   0.8377   0.01270   0.00504  -0.1052   0.4349   0.0647
   2.250   0.8660   0.01228   0.00464  -0.1052   0.4288   0.0673
   2.500   0.8937   0.01227   0.00462  -0.1051   0.4221   0.0705
   2.750   0.9216   0.01224   0.00455  -0.1049   0.4152   0.0733
   3.000   0.9494   0.01203   0.00432  -0.1048   0.4069   0.0760
   3.250   0.9770   0.01200   0.00430  -0.1047   0.3981   0.0794
   3.500   1.0045   0.01200   0.00427  -0.1046   0.3875   0.0822
   3.750   1.0321   0.01204   0.00429  -0.1044   0.3760   0.0847
   4.000   1.0595   0.01196   0.00420  -0.1044   0.3625   0.0885
   4.250   1.0866   0.01205   0.00425  -0.1042   0.3448   0.0918
   4.500   1.1128   0.01227   0.00436  -0.1039   0.3207   0.0954
   4.750   1.1384   0.01255   0.00450  -0.1037   0.2946   0.1000
   5.000   1.1638   0.01288   0.00473  -0.1033   0.2778   0.1055
   5.250   1.1895   0.01317   0.00498  -0.1030   0.2675   0.1131
   5.500   1.2149   0.01347   0.00528  -0.1027   0.2597   0.1380
   5.750   1.2375   0.01245   0.00565  -0.1020   0.2549   1.0000
   6.000   1.2633   0.01275   0.00590  -0.1016   0.2505   1.0000
   6.250   1.2883   0.01311   0.00621  -0.1012   0.2461   1.0000
   6.500   1.3130   0.01350   0.00655  -0.1008   0.2418   1.0000
   6.750   1.3389   0.01374   0.00680  -0.1005   0.2390   1.0000
   7.000   1.3642   0.01403   0.00711  -0.1001   0.2363   1.0000
   7.250   1.3890   0.01436   0.00743  -0.0997   0.2336   1.0000
   7.500   1.4131   0.01474   0.00779  -0.0992   0.2308   1.0000
   7.750   1.4360   0.01523   0.00824  -0.0985   0.2272   1.0000
   8.000   1.4609   0.01549   0.00855  -0.0981   0.2244   1.0000
   8.250   1.4857   0.01575   0.00885  -0.0977   0.2210   1.0000
   8.500   1.5094   0.01609   0.00920  -0.0972   0.2173   1.0000
   8.750   1.5316   0.01654   0.00964  -0.0965   0.2136   1.0000
   9.000   1.5533   0.01703   0.01013  -0.0957   0.2099   1.0000
   9.250   1.5777   0.01725   0.01042  -0.0953   0.2072   1.0000
   9.500   1.6010   0.01754   0.01076  -0.0948   0.2038   1.0000
   9.750   1.6227   0.01794   0.01116  -0.0940   0.1995   1.0000
  10.000   1.6416   0.01853   0.01173  -0.0929   0.1948   1.0000
  10.250   1.6657   0.01869   0.01199  -0.0925   0.1911   1.0000
  10.500   1.6873   0.01902   0.01236  -0.0917   0.1858   1.0000
  10.750   1.7052   0.01958   0.01289  -0.0905   0.1802   1.0000
  11.000   1.7271   0.01984   0.01323  -0.0898   0.1745   1.0000
  11.250   1.7430   0.02037   0.01374  -0.0883   0.1664   1.0000
  11.500   1.7587   0.02090   0.01428  -0.0868   0.1552   1.0000
  11.750   1.7689   0.02180   0.01509  -0.0847   0.1417   1.0000
  12.000   1.7755   0.02300   0.01623  -0.0825   0.1301   1.0000
  12.250   1.7811   0.02435   0.01756  -0.0804   0.1214   1.0000
  12.500   1.7848   0.02596   0.01916  -0.0785   0.1137   1.0000
  12.750   1.7872   0.02780   0.02100  -0.0767   0.1057   1.0000
  13.000   1.7908   0.02964   0.02286  -0.0753   0.0977   1.0000
  13.250   1.7908   0.03193   0.02514  -0.0739   0.0880   1.0000
  13.500   1.7789   0.03552   0.02862  -0.0725   0.0668   1.0000
  13.750   1.7514   0.04108   0.03405  -0.0714   0.0418   1.0000
  14.000   1.7275   0.04669   0.03967  -0.0710   0.0275   1.0000
  14.250   1.7141   0.05123   0.04429  -0.0709   0.0237   1.0000
  14.500   1.7040   0.05543   0.04859  -0.0710   0.0218   1.0000
  14.750   1.6961   0.05942   0.05270  -0.0711   0.0209   1.0000
  15.000   1.6870   0.06371   0.05711  -0.0714   0.0202   1.0000
  15.250   1.6764   0.06830   0.06181  -0.0718   0.0196   1.0000
  15.500   1.6646   0.07316   0.06681  -0.0725   0.0191   1.0000
  15.750   1.6515   0.07835   0.07213  -0.0734   0.0187   1.0000
  16.250   1.6254   0.08903   0.08306  -0.0756   0.0182   1.0000
  16.500   1.6130   0.09441   0.08858  -0.0768   0.0180   1.0000
  16.750   1.5996   0.10000   0.09430  -0.0782   0.0178   1.0000
  17.000   1.5852   0.10582   0.10025  -0.0798   0.0176   1.0000
  17.250   1.5701   0.11188   0.10644  -0.0816   0.0175   1.0000
  17.500   1.5550   0.11804   0.11273  -0.0836   0.0173   1.0000
  17.750   1.5395   0.12434   0.11915  -0.0858   0.0172   1.0000
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