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GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 429 AIRFOIL (goe429-il)
Reynolds number: 100,000
Max Cl/Cd: 37.57 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe429-il-100000-n5.txt
Download as CSV file: xf-goe429-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 429 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -1.0197   0.09564   0.09016   0.0180   1.0000   0.0322
 -14.000  -1.0454   0.08653   0.08085   0.0123   1.0000   0.0321
 -13.750  -1.0675   0.07852   0.07262   0.0074   1.0000   0.0322
 -13.500  -1.0816   0.07234   0.06631   0.0037   1.0000   0.0325
 -13.250  -1.0911   0.06717   0.06104   0.0006   1.0000   0.0330
 -13.000  -1.0995   0.06235   0.05610  -0.0022   1.0000   0.0336
 -12.750  -1.1067   0.05790   0.05152  -0.0047   1.0000   0.0343
 -12.500  -1.1125   0.05381   0.04727  -0.0068   1.0000   0.0353
 -12.250  -1.1170   0.05004   0.04329  -0.0084   1.0000   0.0364
 -12.000  -1.1200   0.04655   0.03953  -0.0094   1.0000   0.0378
 -11.750  -1.1205   0.04365   0.03646  -0.0096   1.0000   0.0391
 -11.500  -1.1181   0.04158   0.03433  -0.0091   1.0000   0.0405
 -11.250  -1.1108   0.03961   0.03222  -0.0087   1.0000   0.0427
 -11.000  -1.1009   0.03752   0.02985  -0.0081   1.0000   0.0462
 -10.750  -1.0884   0.03606   0.02836  -0.0077   1.0000   0.0490
 -10.500  -1.0735   0.03450   0.02659  -0.0072   1.0000   0.0534
 -10.250  -1.0573   0.03309   0.02509  -0.0068   1.0000   0.0575
 -10.000  -1.0388   0.03191   0.02375  -0.0064   1.0000   0.0627
  -9.750  -1.0196   0.03071   0.02242  -0.0061   1.0000   0.0676
  -9.500  -0.9989   0.02973   0.02129  -0.0058   1.0000   0.0733
  -9.250  -0.9778   0.02866   0.02007  -0.0055   1.0000   0.0789
  -9.000  -0.9557   0.02781   0.01913  -0.0053   1.0000   0.0854
  -8.750  -0.9333   0.02681   0.01800  -0.0051   1.0000   0.0918
  -8.500  -0.9103   0.02588   0.01699  -0.0049   1.0000   0.0979
  -8.250  -0.8861   0.02496   0.01588  -0.0046   1.0000   0.1035
  -8.000  -0.8632   0.02387   0.01485  -0.0043   1.0000   0.1088
  -7.750  -0.8387   0.02300   0.01389  -0.0041   1.0000   0.1147
  -7.500  -0.8145   0.02208   0.01295  -0.0039   1.0000   0.1207
  -7.250  -0.7898   0.02126   0.01210  -0.0037   1.0000   0.1276
  -7.000  -0.7647   0.02046   0.01131  -0.0035   1.0000   0.1352
  -6.750  -0.7392   0.01974   0.01059  -0.0034   1.0000   0.1452
  -6.500  -0.7136   0.01904   0.00994  -0.0034   1.0000   0.1574
  -6.250  -0.6873   0.01841   0.00935  -0.0034   1.0000   0.1742
  -6.000  -0.6610   0.01779   0.00881  -0.0034   1.0000   0.1956
  -5.750  -0.6343   0.01724   0.00827  -0.0035   1.0000   0.2196
  -5.500  -0.6076   0.01669   0.00781  -0.0035   1.0000   0.2429
  -5.250  -0.5805   0.01621   0.00739  -0.0036   1.0000   0.2671
  -5.000  -0.5533   0.01577   0.00703  -0.0037   1.0000   0.2903
  -4.750  -0.5259   0.01539   0.00672  -0.0038   1.0000   0.3139
  -4.500  -0.4983   0.01504   0.00645  -0.0039   1.0000   0.3377
  -4.250  -0.4705   0.01474   0.00620  -0.0040   1.0000   0.3617
  -4.000  -0.4427   0.01445   0.00600  -0.0041   1.0000   0.3851
  -3.750  -0.4149   0.01419   0.00582  -0.0042   1.0000   0.4113
  -3.500  -0.3874   0.01394   0.00570  -0.0043   1.0000   0.4370
  -3.250  -0.3602   0.01374   0.00560  -0.0044   1.0000   0.4634
  -3.000  -0.3305   0.01358   0.00555  -0.0050   0.9877   0.4895
  -2.750  -0.2924   0.01347   0.00552  -0.0071   0.9604   0.5144
  -2.500  -0.2564   0.01341   0.00551  -0.0085   0.9363   0.5363
  -2.250  -0.2243   0.01340   0.00550  -0.0090   0.9133   0.5560
  -2.000  -0.1963   0.01341   0.00551  -0.0085   0.8910   0.5743
  -1.750  -0.1701   0.01343   0.00553  -0.0076   0.8708   0.5913
  -1.500  -0.1444   0.01346   0.00554  -0.0066   0.8521   0.6080
  -1.250  -0.1191   0.01349   0.00555  -0.0055   0.8339   0.6250
  -1.000  -0.0936   0.01350   0.00554  -0.0045   0.8148   0.6416
  -0.750  -0.0681   0.01351   0.00552  -0.0035   0.7950   0.6578
  -0.500  -0.0426   0.01351   0.00549  -0.0024   0.7754   0.6737
  -0.250  -0.0171   0.01351   0.00547  -0.0013   0.7566   0.6901
   0.000   0.0082   0.01351   0.00547  -0.0002   0.7384   0.7083
   0.250   0.0334   0.01351   0.00546   0.0010   0.7202   0.7274
   0.500   0.0589   0.01348   0.00545   0.0020   0.7009   0.7456
   0.750   0.0849   0.01345   0.00543   0.0029   0.6795   0.7610
   1.000   0.1109   0.01341   0.00539   0.0038   0.6569   0.7753
   1.250   0.1372   0.01336   0.00535   0.0046   0.6315   0.7900
   1.500   0.1632   0.01333   0.00530   0.0055   0.6030   0.8052
   1.750   0.1892   0.01330   0.00526   0.0064   0.5697   0.8213
   2.000   0.2150   0.01330   0.00522   0.0073   0.5305   0.8390
   2.250   0.2407   0.01336   0.00518   0.0082   0.4872   0.8590
   2.500   0.2675   0.01351   0.00519   0.0088   0.4435   0.8826
   2.750   0.2978   0.01373   0.00528   0.0086   0.4030   0.9126
   3.000   0.3333   0.01402   0.00544   0.0070   0.3661   0.9520
   3.250   0.3687   0.01435   0.00563   0.0053   0.3350   1.0000
   3.500   0.3965   0.01473   0.00587   0.0049   0.3120   1.0000
   3.750   0.4243   0.01511   0.00615   0.0047   0.2930   1.0000
   4.000   0.4521   0.01551   0.00645   0.0045   0.2762   1.0000
   4.250   0.4797   0.01591   0.00677   0.0043   0.2591   1.0000
   4.500   0.5072   0.01630   0.00707   0.0041   0.2415   1.0000
   4.750   0.5347   0.01669   0.00739   0.0040   0.2259   1.0000
   5.000   0.5622   0.01709   0.00776   0.0039   0.2147   1.0000
   5.250   0.5894   0.01750   0.00813   0.0038   0.2036   1.0000
   5.500   0.6170   0.01785   0.00853   0.0037   0.1915   1.0000
   5.750   0.6444   0.01823   0.00897   0.0037   0.1818   1.0000
   6.000   0.6715   0.01864   0.00939   0.0036   0.1711   1.0000
   6.250   0.6986   0.01903   0.00981   0.0036   0.1558   1.0000
   6.500   0.7256   0.01946   0.01029   0.0036   0.1379   1.0000
   6.750   0.7519   0.02002   0.01081   0.0035   0.1149   1.0000
   7.000   0.7778   0.02070   0.01146   0.0036   0.0912   1.0000
   7.250   0.8026   0.02157   0.01221   0.0037   0.0770   1.0000
   7.500   0.8270   0.02248   0.01309   0.0038   0.0711   1.0000
   7.750   0.8505   0.02351   0.01412   0.0040   0.0672   1.0000
   8.000   0.8739   0.02450   0.01518   0.0042   0.0644   1.0000
   8.250   0.8966   0.02555   0.01633   0.0045   0.0616   1.0000
   8.500   0.9182   0.02671   0.01756   0.0048   0.0594   1.0000
   8.750   0.9386   0.02799   0.01891   0.0052   0.0578   1.0000
   9.000   0.9581   0.02941   0.02034   0.0057   0.0565   1.0000
   9.250   0.9789   0.03065   0.02175   0.0063   0.0555   1.0000
   9.500   0.9989   0.03200   0.02325   0.0068   0.0543   1.0000
   9.750   1.0180   0.03345   0.02486   0.0073   0.0529   1.0000
  10.000   1.0360   0.03499   0.02655   0.0079   0.0514   1.0000
  10.250   1.0532   0.03664   0.02832   0.0084   0.0502   1.0000
  10.500   1.0696   0.03843   0.03022   0.0090   0.0492   1.0000
  10.750   1.0850   0.04038   0.03224   0.0096   0.0482   1.0000
  11.000   1.0995   0.04285   0.03475   0.0102   0.0470   1.0000
  11.250   1.1083   0.04507   0.03729   0.0108   0.0461   1.0000
  11.500   1.1130   0.04749   0.04003   0.0114   0.0453   1.0000
  11.750   1.1127   0.05017   0.04300   0.0121   0.0447   1.0000
  12.000   1.1072   0.05324   0.04634   0.0124   0.0442   1.0000
  12.250   1.0984   0.05693   0.05028   0.0116   0.0437   1.0000
  12.500   1.0860   0.06136   0.05497   0.0096   0.0434   1.0000
  12.750   1.0696   0.06677   0.06063   0.0065   0.0431   1.0000
  13.000   1.0472   0.07366   0.06777   0.0018   0.0431   1.0000
  13.250   1.0145   0.08323   0.07762  -0.0055   0.0433   1.0000
  13.500   0.9572   0.09937   0.09403  -0.0177   0.0443   1.0000
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