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GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 526 AIRFOIL (goe526-il)
Reynolds number: 100,000
Max Cl/Cd: 52.85 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe526-il-100000-n5.txt
Download as CSV file: xf-goe526-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 526 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3388   0.09678   0.09150  -0.0432   1.0000   0.0581
  -9.250  -0.3511   0.09441   0.08922  -0.0419   1.0000   0.0582
  -9.000  -0.3586   0.09149   0.08637  -0.0422   0.9982   0.0585
  -8.750  -0.3500   0.08615   0.08102  -0.0483   0.9902   0.0587
  -8.500  -0.3435   0.08043   0.07529  -0.0552   0.9815   0.0587
  -8.250  -0.3425   0.07399   0.06883  -0.0632   0.9701   0.0582
  -8.000  -0.3415   0.06642   0.06116  -0.0716   0.9574   0.0580
  -7.750  -0.3440   0.05815   0.05268  -0.0788   0.9449   0.0580
  -7.500  -0.3484   0.04935   0.04346  -0.0838   0.9333   0.0590
  -7.250  -0.3493   0.04063   0.03395  -0.0869   0.9247   0.0605
  -7.000  -0.3476   0.03591   0.02853  -0.0856   0.9136   0.0614
  -6.750  -0.3259   0.03303   0.02520  -0.0861   0.9087   0.0624
  -6.500  -0.3057   0.03185   0.02389  -0.0854   0.9012   0.0634
  -6.250  -0.2807   0.03077   0.02267  -0.0854   0.8953   0.0651
  -6.000  -0.2525   0.02920   0.02080  -0.0861   0.8913   0.0673
  -5.750  -0.2341   0.02768   0.01889  -0.0847   0.8838   0.0693
  -5.500  -0.2087   0.02631   0.01722  -0.0845   0.8783   0.0710
  -5.250  -0.1777   0.02545   0.01631  -0.0853   0.8746   0.0728
  -5.000  -0.1546   0.02481   0.01558  -0.0845   0.8681   0.0753
  -4.750  -0.1289   0.02399   0.01450  -0.0841   0.8624   0.0788
  -4.500  -0.0984   0.02321   0.01367  -0.0846   0.8583   0.0818
  -4.250  -0.0706   0.02267   0.01308  -0.0845   0.8535   0.0850
  -4.000  -0.0474   0.02218   0.01245  -0.0836   0.8467   0.0891
  -3.500   0.0154   0.02111   0.01131  -0.0846   0.8384   0.0995
  -3.250   0.0358   0.02078   0.01095  -0.0830   0.8287   0.1048
  -3.000   0.0690   0.02026   0.01040  -0.0836   0.8224   0.1122
  -2.750   0.0925   0.01991   0.01003  -0.0824   0.8125   0.1194
  -2.500   0.1232   0.01949   0.00955  -0.0826   0.8057   0.1291
  -2.250   0.1484   0.01921   0.00932  -0.0819   0.7985   0.1380
  -2.000   0.1740   0.01894   0.00902  -0.0812   0.7912   0.1489
  -1.750   0.2052   0.01860   0.00865  -0.0815   0.7860   0.1618
  -1.500   0.2263   0.01842   0.00855  -0.0801   0.7774   0.1726
  -1.250   0.2542   0.01814   0.00828  -0.0798   0.7709   0.1866
  -1.000   0.2807   0.01792   0.00809  -0.0793   0.7640   0.2017
  -0.750   0.3050   0.01775   0.00796  -0.0784   0.7557   0.2186
  -0.500   0.3359   0.01741   0.00769  -0.0786   0.7499   0.2402
  -0.250   0.3574   0.01728   0.00770  -0.0773   0.7404   0.2662
   0.000   0.3872   0.01689   0.00750  -0.0775   0.7335   0.3182
   0.250   0.4069   0.01623   0.00753  -0.0759   0.7246   0.4865
   0.750   0.5800   0.01524   0.00743  -0.0980   0.7075   1.0000
   1.000   0.6034   0.01527   0.00734  -0.0968   0.6983   1.0000
   1.250   0.6234   0.01539   0.00740  -0.0951   0.6873   1.0000
   1.500   0.6472   0.01541   0.00731  -0.0940   0.6776   1.0000
   1.750   0.6670   0.01553   0.00738  -0.0922   0.6655   1.0000
   2.000   0.6878   0.01563   0.00742  -0.0907   0.6538   1.0000
   2.250   0.7108   0.01569   0.00739  -0.0894   0.6428   1.0000
   2.500   0.7309   0.01582   0.00747  -0.0877   0.6296   1.0000
   2.750   0.7509   0.01594   0.00754  -0.0860   0.6154   1.0000
   3.000   0.7713   0.01605   0.00759  -0.0843   0.6005   1.0000
   3.250   0.7916   0.01618   0.00764  -0.0826   0.5851   1.0000
   3.500   0.8120   0.01633   0.00771  -0.0809   0.5700   1.0000
   3.750   0.8321   0.01649   0.00779  -0.0792   0.5546   1.0000
   4.000   0.8520   0.01669   0.00789  -0.0775   0.5390   1.0000
   4.250   0.8720   0.01690   0.00802  -0.0758   0.5244   1.0000
   4.500   0.8918   0.01716   0.00821  -0.0741   0.5109   1.0000
   4.750   0.9114   0.01743   0.00844  -0.0724   0.4984   1.0000
   5.000   0.9310   0.01772   0.00866  -0.0708   0.4860   1.0000
   5.250   0.9506   0.01803   0.00887  -0.0691   0.4738   1.0000
   5.500   0.9692   0.01836   0.00916  -0.0673   0.4614   1.0000
   5.750   0.9879   0.01871   0.00948  -0.0656   0.4499   1.0000
   6.000   1.0078   0.01907   0.00977  -0.0640   0.4401   1.0000
   6.250   1.0265   0.01943   0.01017  -0.0624   0.4305   1.0000
   6.500   1.0463   0.01981   0.01051  -0.0609   0.4217   1.0000
   6.750   1.0642   0.02020   0.01094  -0.0591   0.4116   1.0000
   7.000   1.0823   0.02061   0.01134  -0.0574   0.4019   1.0000
   7.250   1.0989   0.02102   0.01174  -0.0554   0.3908   1.0000
   7.500   1.1136   0.02144   0.01220  -0.0531   0.3786   1.0000
   7.750   1.1272   0.02187   0.01264  -0.0507   0.3658   1.0000
   8.000   1.1391   0.02233   0.01307  -0.0480   0.3522   1.0000
   8.250   1.1486   0.02279   0.01355  -0.0449   0.3383   1.0000
   8.500   1.1575   0.02328   0.01408  -0.0418   0.3246   1.0000
   8.750   1.1663   0.02383   0.01466  -0.0388   0.3108   1.0000
   9.000   1.1747   0.02443   0.01527  -0.0358   0.2962   1.0000
   9.250   1.1823   0.02512   0.01596  -0.0330   0.2804   1.0000
   9.500   1.1891   0.02590   0.01672  -0.0302   0.2637   1.0000
   9.750   1.1954   0.02679   0.01758  -0.0275   0.2469   1.0000
  10.000   1.2009   0.02779   0.01855  -0.0249   0.2311   1.0000
  10.250   1.2058   0.02890   0.01961  -0.0224   0.2166   1.0000
  10.500   1.2103   0.03013   0.02079  -0.0200   0.2040   1.0000
  10.750   1.2141   0.03147   0.02208  -0.0178   0.1936   1.0000
  11.000   1.2181   0.03289   0.02348  -0.0157   0.1840   1.0000
  11.250   1.2226   0.03435   0.02496  -0.0139   0.1753   1.0000
  11.500   1.2253   0.03599   0.02657  -0.0120   0.1676   1.0000
  11.750   1.2307   0.03752   0.02816  -0.0105   0.1601   1.0000
  12.000   1.2333   0.03929   0.02994  -0.0089   0.1529   1.0000
  12.250   1.2379   0.04098   0.03170  -0.0076   0.1462   1.0000
  12.500   1.2415   0.04279   0.03359  -0.0064   0.1394   1.0000
  12.750   1.2444   0.04471   0.03552  -0.0052   0.1338   1.0000
  13.000   1.2486   0.04659   0.03754  -0.0042   0.1273   1.0000
  13.250   1.2501   0.04871   0.03967  -0.0033   0.1225   1.0000
  13.500   1.2539   0.05075   0.04183  -0.0025   0.1172   1.0000
  13.750   1.2562   0.05296   0.04411  -0.0019   0.1125   1.0000
  14.000   1.2569   0.05533   0.04647  -0.0013   0.1090   1.0000
  14.250   1.2605   0.05759   0.04889  -0.0008   0.1046   1.0000
  14.500   1.2620   0.06005   0.05144  -0.0005   0.1010   1.0000
  14.750   1.2625   0.06265   0.05404  -0.0003   0.0980   1.0000
  15.000   1.2652   0.06513   0.05662  -0.0001   0.0949   1.0000
  15.250   1.2668   0.06780   0.05941  -0.0001   0.0919   1.0000
  15.500   1.2678   0.07056   0.06224  -0.0002   0.0893   1.0000
  15.750   1.2699   0.07315   0.06482  -0.0002   0.0870   1.0000
  16.000   1.2712   0.07601   0.06781  -0.0004   0.0846   1.0000
  16.250   1.2715   0.07909   0.07104  -0.0007   0.0822   1.0000
  16.500   1.2716   0.08219   0.07424  -0.0012   0.0800   1.0000
  16.750   1.2727   0.08514   0.07723  -0.0017   0.0780   1.0000
  17.000   1.2766   0.08762   0.07971  -0.0019   0.0760   1.0000
  17.250   1.2708   0.09189   0.08422  -0.0031   0.0743   1.0000
  17.500   1.2655   0.09610   0.08862  -0.0045   0.0725   1.0000
  17.750   1.2610   0.10021   0.09287  -0.0059   0.0707   1.0000
  18.000   1.2590   0.10389   0.09664  -0.0071   0.0691   1.0000
  18.250   1.2638   0.10631   0.09903  -0.0077   0.0673   1.0000
  18.500   1.2541   0.11151   0.10441  -0.0099   0.0661   1.0000
  18.750   1.2365   0.11835   0.11152  -0.0133   0.0649   1.0000
  19.000   1.2164   0.12585   0.11926  -0.0172   0.0637   1.0000
  19.250   1.1929   0.13431   0.12794  -0.0220   0.0627   1.0000
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