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GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 429 AIRFOIL (goe429-il)
Reynolds number: 50,000
Max Cl/Cd: 26.9 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe429-il-50000-n5.txt
Download as CSV file: xf-goe429-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8610   0.10084   0.09378   0.0158   1.0000   0.0759
 -12.000  -0.9023   0.08763   0.08049   0.0067   1.0000   0.0752
 -11.750  -0.9393   0.07703   0.06975  -0.0010   1.0000   0.0745
 -11.500  -0.9702   0.06893   0.06142  -0.0065   1.0000   0.0743
 -11.250  -0.9957   0.06275   0.05494  -0.0098   1.0000   0.0749
 -11.000  -1.0165   0.05770   0.04945  -0.0107   1.0000   0.0762
 -10.750  -1.0057   0.05575   0.04759  -0.0102   1.0000   0.0801
 -10.500  -1.0033   0.05278   0.04439  -0.0102   1.0000   0.0844
 -10.250  -1.0059   0.04888   0.03985  -0.0102   1.0000   0.0890
 -10.000  -0.9890   0.04728   0.03838  -0.0098   1.0000   0.0947
  -9.750  -0.9797   0.04456   0.03522  -0.0096   1.0000   0.1014
  -9.500  -0.9628   0.04262   0.03326  -0.0092   1.0000   0.1077
  -9.250  -0.9465   0.04049   0.03084  -0.0088   1.0000   0.1147
  -9.000  -0.9275   0.03860   0.02884  -0.0085   1.0000   0.1212
  -8.750  -0.9074   0.03691   0.02694  -0.0081   1.0000   0.1283
  -8.500  -0.8863   0.03525   0.02515  -0.0078   1.0000   0.1352
  -8.250  -0.8644   0.03385   0.02362  -0.0074   1.0000   0.1429
  -8.000  -0.8417   0.03249   0.02219  -0.0070   1.0000   0.1502
  -7.750  -0.8186   0.03121   0.02068  -0.0067   1.0000   0.1596
  -7.500  -0.7953   0.03011   0.01962  -0.0064   1.0000   0.1685
  -7.250  -0.7715   0.02897   0.01841  -0.0061   1.0000   0.1790
  -7.000  -0.7476   0.02789   0.01727  -0.0058   1.0000   0.1922
  -6.750  -0.7236   0.02683   0.01616  -0.0055   1.0000   0.2072
  -6.500  -0.6997   0.02582   0.01519  -0.0052   1.0000   0.2250
  -6.250  -0.6758   0.02487   0.01430  -0.0049   1.0000   0.2467
  -6.000  -0.6515   0.02400   0.01348  -0.0046   1.0000   0.2713
  -5.750  -0.6270   0.02328   0.01282  -0.0043   1.0000   0.2976
  -5.500  -0.6021   0.02267   0.01229  -0.0040   1.0000   0.3242
  -5.250  -0.5767   0.02214   0.01178  -0.0037   1.0000   0.3509
  -5.000  -0.5510   0.02167   0.01132  -0.0034   1.0000   0.3775
  -4.750  -0.5253   0.02126   0.01096  -0.0030   1.0000   0.4025
  -4.500  -0.4994   0.02089   0.01063  -0.0027   1.0000   0.4302
  -4.250  -0.4740   0.02060   0.01040  -0.0022   1.0000   0.4609
  -4.000  -0.4489   0.02037   0.01029  -0.0014   1.0000   0.4894
  -3.750  -0.4235   0.02013   0.01014  -0.0007   1.0000   0.5142
  -3.500  -0.3978   0.01988   0.00993  -0.0002   1.0000   0.5357
  -3.250  -0.3721   0.01963   0.00970   0.0003   1.0000   0.5565
  -3.000  -0.3469   0.01944   0.00956   0.0008   1.0000   0.5759
  -2.750  -0.3224   0.01929   0.00945   0.0015   1.0000   0.5948
  -2.500  -0.2989   0.01915   0.00935   0.0022   1.0000   0.6139
  -2.250  -0.2769   0.01902   0.00926   0.0030   1.0000   0.6333
  -2.000  -0.2566   0.01893   0.00917   0.0039   1.0000   0.6531
  -1.750  -0.2375   0.01887   0.00916   0.0051   1.0000   0.6716
  -1.500  -0.2052   0.01886   0.00918   0.0039   0.9885   0.6921
  -1.250  -0.1616   0.01885   0.00918   0.0008   0.9696   0.7160
  -1.000  -0.1213   0.01884   0.00924  -0.0012   0.9499   0.7384
  -0.750  -0.0828   0.01882   0.00927  -0.0027   0.9304   0.7616
  -0.500  -0.0487   0.01879   0.00929  -0.0032   0.9095   0.7835
  -0.250  -0.0184   0.01875   0.00930  -0.0028   0.8873   0.8034
   0.000   0.0101   0.01871   0.00928  -0.0018   0.8651   0.8229
   0.250   0.0356   0.01865   0.00926  -0.0004   0.8406   0.8429
   0.500   0.0615   0.01857   0.00920   0.0011   0.8171   0.8632
   0.750   0.0892   0.01849   0.00914   0.0022   0.7912   0.8837
   1.000   0.1195   0.01840   0.00905   0.0028   0.7662   0.9058
   1.250   0.1530   0.01833   0.00898   0.0026   0.7386   0.9293
   1.500   0.1904   0.01827   0.00889   0.0014   0.7084   0.9537
   1.750   0.2291   0.01821   0.00880  -0.0003   0.6751   0.9811
   2.000   0.2597   0.01818   0.00869  -0.0009   0.6408   1.0000
   2.250   0.2799   0.01822   0.00863   0.0003   0.6068   1.0000
   2.500   0.3025   0.01832   0.00860   0.0012   0.5685   1.0000
   2.750   0.3262   0.01847   0.00858   0.0021   0.5276   1.0000
   3.000   0.3505   0.01873   0.00863   0.0028   0.4866   1.0000
   3.250   0.3753   0.01910   0.00874   0.0035   0.4485   1.0000
   3.500   0.4006   0.01957   0.00899   0.0039   0.4157   1.0000
   3.750   0.4264   0.02012   0.00938   0.0041   0.3880   1.0000
   4.000   0.4526   0.02071   0.00982   0.0042   0.3652   1.0000
   4.250   0.4793   0.02132   0.01034   0.0043   0.3465   1.0000
   4.500   0.5060   0.02196   0.01093   0.0044   0.3313   1.0000
   4.750   0.5329   0.02262   0.01160   0.0044   0.3174   1.0000
   5.000   0.5599   0.02329   0.01232   0.0045   0.3049   1.0000
   5.250   0.5864   0.02397   0.01303   0.0046   0.2923   1.0000
   5.500   0.6123   0.02459   0.01366   0.0047   0.2772   1.0000
   5.750   0.6377   0.02516   0.01425   0.0049   0.2605   1.0000
   6.000   0.6628   0.02573   0.01488   0.0050   0.2443   1.0000
   6.250   0.6877   0.02632   0.01553   0.0051   0.2283   1.0000
   6.500   0.7124   0.02695   0.01624   0.0052   0.2127   1.0000
   6.750   0.7364   0.02757   0.01697   0.0054   0.1943   1.0000
   7.000   0.7598   0.02825   0.01773   0.0055   0.1755   1.0000
   7.250   0.7826   0.02910   0.01862   0.0057   0.1574   1.0000
   7.500   0.8051   0.03023   0.01990   0.0060   0.1378   1.0000
   7.750   0.8265   0.03153   0.02127   0.0063   0.1219   1.0000
   8.000   0.8473   0.03289   0.02264   0.0067   0.1106   1.0000
   8.250   0.8677   0.03428   0.02407   0.0070   0.1019   1.0000
   8.500   0.8879   0.03595   0.02590   0.0075   0.0959   1.0000
   8.750   0.9073   0.03766   0.02776   0.0080   0.0915   1.0000
   9.000   0.9259   0.03927   0.02941   0.0084   0.0885   1.0000
   9.250   0.9430   0.04150   0.03192   0.0089   0.0854   1.0000
   9.500   0.9580   0.04378   0.03447   0.0093   0.0823   1.0000
   9.750   0.9721   0.04577   0.03659   0.0096   0.0795   1.0000
  10.000   0.9867   0.04751   0.03833   0.0101   0.0773   1.0000
  10.250   0.9931   0.05084   0.04202   0.0103   0.0759   1.0000
  10.500   0.9933   0.05469   0.04627   0.0103   0.0749   1.0000
  10.750   0.9851   0.05907   0.05099   0.0098   0.0742   1.0000
  11.000   0.9656   0.06440   0.05661   0.0081   0.0740   1.0000
  11.250   0.9343   0.07230   0.06475   0.0030   0.0742   1.0000
  11.500   0.8841   0.08545   0.07811  -0.0070   0.0751   1.0000
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