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GOE 424 AIRFOIL (goe424-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 424 AIRFOIL (goe424-il)
Reynolds number: 50,000
Max Cl/Cd: 16.22 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe424-il-50000-n5.txt
Download as CSV file: xf-goe424-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 424 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3790   0.08695   0.08038  -0.0827   0.9737   0.0732
 -10.750  -0.3985   0.07966   0.07294  -0.0893   0.9610   0.0728
 -10.500  -0.4206   0.07397   0.06703  -0.0932   0.9458   0.0726
 -10.250  -0.4409   0.06959   0.06238  -0.0940   0.9285   0.0726
  -9.750  -0.4651   0.06174   0.05370  -0.0931   0.8951   0.0734
  -9.500  -0.4536   0.05875   0.05056  -0.0931   0.8813   0.0744
  -9.250  -0.4413   0.05593   0.04750  -0.0929   0.8682   0.0752
  -9.000  -0.4262   0.05298   0.04421  -0.0929   0.8572   0.0759
  -8.750  -0.4119   0.05065   0.04161  -0.0922   0.8441   0.0773
  -8.500  -0.3979   0.04854   0.03917  -0.0912   0.8309   0.0789
  -8.250  -0.3796   0.04635   0.03657  -0.0906   0.8199   0.0805
  -8.000  -0.3581   0.04430   0.03407  -0.0902   0.8094   0.0817
  -7.750  -0.3381   0.04265   0.03203  -0.0893   0.7975   0.0826
  -7.500  -0.3061   0.04076   0.03000  -0.0903   0.7898   0.0848
  -7.250  -0.2835   0.03958   0.02871  -0.0897   0.7780   0.0870
  -7.000  -0.2497   0.03810   0.02700  -0.0906   0.7712   0.0893
  -6.750  -0.2263   0.03719   0.02592  -0.0898   0.7599   0.0908
  -6.500  -0.1923   0.03607   0.02452  -0.0905   0.7533   0.0934
  -6.250  -0.1695   0.03531   0.02376  -0.0898   0.7430   0.0960
  -6.000  -0.1392   0.03437   0.02273  -0.0901   0.7365   0.0993
  -5.750  -0.1187   0.03387   0.02214  -0.0889   0.7277   0.1017
  -5.500  -0.0941   0.03326   0.02134  -0.0883   0.7211   0.1046
  -5.250  -0.0725   0.03266   0.02064  -0.0875   0.7149   0.1085
  -5.000  -0.0568   0.03221   0.02017  -0.0859   0.7073   0.1129
  -4.750  -0.0339   0.03161   0.01942  -0.0852   0.7020   0.1187
  -4.500  -0.0176   0.03122   0.01901  -0.0837   0.6955   0.1242
  -4.250  -0.0007   0.03080   0.01861  -0.0823   0.6892   0.1337
  -4.000   0.0204   0.02998   0.01804  -0.0817   0.6847   0.1605
  -3.750   0.0345   0.02917   0.01773  -0.0802   0.6798   0.2546
  -3.500   0.0405   0.02879   0.01814  -0.0769   0.6738   0.4115
  -3.250   0.0583   0.02871   0.01832  -0.0748   0.6693   0.4974
  -3.000   0.0817   0.02868   0.01836  -0.0732   0.6657   0.5641
  -2.750   0.0922   0.02920   0.01900  -0.0701   0.6598   0.6094
  -2.500   0.1077   0.02961   0.01945  -0.0675   0.6547   0.6523
  -2.250   0.1302   0.02987   0.01969  -0.0658   0.6509   0.6909
  -2.000   0.1581   0.03008   0.01985  -0.0648   0.6481   0.7264
  -1.750   0.1701   0.03085   0.02066  -0.0620   0.6428   0.7537
  -1.500   0.1855   0.03152   0.02133  -0.0596   0.6377   0.7831
  -1.250   0.2147   0.03200   0.02174  -0.0588   0.6340   0.8153
  -1.000   0.2513   0.03231   0.02191  -0.0595   0.6311   0.8456
  -0.750   0.2868   0.03283   0.02228  -0.0608   0.6278   0.8675
  -0.500   0.3002   0.03400   0.02347  -0.0597   0.6218   0.8871
  -0.250   0.3340   0.03455   0.02387  -0.0615   0.6176   0.9046
   0.000   0.3778   0.03479   0.02393  -0.0649   0.6145   0.9207
   0.250   0.4266   0.03489   0.02382  -0.0690   0.6120   0.9357
   0.500   0.4527   0.03628   0.02520  -0.0710   0.6066   0.9533
   0.750   0.4871   0.03734   0.02621  -0.0743   0.6015   0.9697
   1.000   0.5343   0.03774   0.02648  -0.0790   0.5979   0.9838
   1.250   0.5875   0.03785   0.02644  -0.0845   0.5952   0.9964
   1.500   0.6149   0.03792   0.02636  -0.0852   0.5929   1.0000
   1.750   0.5015   0.04206   0.03071  -0.0667   0.5816   1.0000
   2.000   0.5073   0.04261   0.03114  -0.0639   0.5780   1.0000
   2.250   0.5303   0.04278   0.03116  -0.0633   0.5756   1.0000
   3.750   0.4918   0.05464   0.04270  -0.0447   0.5389   1.0000
   4.250   0.4823   0.05976   0.04778  -0.0413   0.5240   1.0000
   4.500   0.5102   0.06009   0.04803  -0.0413   0.5212   1.0000
   5.000   0.5090   0.06480   0.05271  -0.0388   0.5066   1.0000
   5.250   0.5370   0.06514   0.05299  -0.0388   0.5036   1.0000
   5.750   0.5409   0.06958   0.05742  -0.0368   0.4889   1.0000
   6.000   0.5694   0.06985   0.05764  -0.0368   0.4859   1.0000
   6.250   0.5559   0.07329   0.06111  -0.0354   0.4757   1.0000
   6.500   0.5764   0.07412   0.06192  -0.0351   0.4709   1.0000
   6.750   0.6062   0.07424   0.06200  -0.0351   0.4681   1.0000
   7.000   0.5899   0.07797   0.06578  -0.0339   0.4568   1.0000
   7.250   0.6148   0.07842   0.06621  -0.0337   0.4528   1.0000
   7.750   0.6268   0.08245   0.07027  -0.0326   0.4381   1.0000
   8.000   0.6550   0.08259   0.07040  -0.0325   0.4350   1.0000
   8.250   0.6418   0.08630   0.07416  -0.0317   0.4239   1.0000
   8.500   0.6657   0.08680   0.07467  -0.0315   0.4201   1.0000
   9.000   0.6771   0.09108   0.07901  -0.0308   0.4055   1.0000
   9.250   0.7040   0.09126   0.07920  -0.0306   0.4027   1.0000
   9.500   0.6886   0.09556   0.08357  -0.0303   0.3916   1.0000
   9.750   0.7127   0.09594   0.08397  -0.0301   0.3881   1.0000
  10.000   0.7022   0.09990   0.08799  -0.0300   0.3782   1.0000
  10.250   0.7209   0.10091   0.08902  -0.0298   0.3740   1.0000
  10.500   0.7444   0.10137   0.08952  -0.0296   0.3712   1.0000
  10.750   0.7287   0.10612   0.09434  -0.0298   0.3606   1.0000
  11.000   0.7515   0.10658   0.09483  -0.0296   0.3573   1.0000
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