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GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 256 (JUNKERS E) AIRFOIL (goe256-il)
Reynolds number: 100,000
Max Cl/Cd: 45.18 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe256-il-100000.txt
Download as CSV file: xf-goe256-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 256 (JUNKERS E) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2897   0.11186   0.10715  -0.0494   0.9743   0.1303
  -8.500  -0.3015   0.10891   0.10422  -0.0555   0.9694   0.1365
  -8.250  -0.3589   0.10754   0.10293  -0.0591   0.9590   0.1377
  -8.000  -0.3098   0.10211   0.09748  -0.0577   0.9585   0.1405
  -7.750  -0.2806   0.09914   0.09448  -0.0584   0.9560   0.1443
  -7.500  -0.2855   0.09697   0.09234  -0.0583   0.9499   0.1479
  -7.250  -0.3160   0.09448   0.08987  -0.0605   0.9417   0.1524
  -7.000  -0.3655   0.09043   0.08573  -0.0639   0.9309   0.1558
  -6.750  -0.3301   0.08763   0.08302  -0.0617   0.9282   0.1583
  -6.500  -0.3047   0.08495   0.08033  -0.0628   0.9244   0.1634
  -6.250  -0.3550   0.08188   0.07695  -0.0653   0.9125   0.1731
  -6.000  -0.3201   0.07845   0.07370  -0.0644   0.9092   0.1760
  -5.750  -0.3344   0.07730   0.07214  -0.0662   0.9002   0.1905
  -5.500  -0.3108   0.07332   0.06842  -0.0643   0.8951   0.1932
  -5.250  -0.2809   0.07104   0.06616  -0.0653   0.8904   0.2020
  -5.000  -0.2783   0.06838   0.06340  -0.0649   0.8827   0.2130
  -4.750  -0.2691   0.06613   0.06100  -0.0652   0.8749   0.2289
  -4.500  -0.2365   0.06341   0.05820  -0.0678   0.8707   0.2473
  -4.250  -0.2334   0.05159   0.04426  -0.0699   0.8616   0.1382
  -4.000  -0.2025   0.05146   0.04488  -0.0716   0.8557   0.1689
  -3.750  -0.1589   0.04417   0.03572  -0.0736   0.8528   0.1223
  -3.500  -0.1493   0.04311   0.03445  -0.0709   0.8426   0.1224
  -3.250  -0.1120   0.04055   0.03177  -0.0731   0.8378   0.1251
  -3.000  -0.0637   0.03884   0.02985  -0.0763   0.8345   0.1278
  -2.750  -0.0547   0.03838   0.02925  -0.0734   0.8229   0.1290
  -2.500  -0.0102   0.03718   0.02778  -0.0757   0.8186   0.1342
  -2.250   0.0082   0.03691   0.02727  -0.0740   0.8083   0.1371
  -2.000   0.0488   0.03546   0.02578  -0.0759   0.8029   0.1420
  -1.750   0.0981   0.03429   0.02456  -0.0790   0.7999   0.1503
  -1.500   0.1104   0.03431   0.02447  -0.0764   0.7873   0.1541
  -1.250   0.1574   0.03291   0.02320  -0.0790   0.7838   0.1641
  -1.000   0.1748   0.03286   0.02312  -0.0772   0.7724   0.1708
  -0.750   0.2171   0.03167   0.02209  -0.0790   0.7678   0.1843
  -0.500   0.2669   0.03031   0.02086  -0.0817   0.7655   0.2055
   0.250   0.5126   0.02612   0.01893  -0.1090   0.7535   1.0000
   0.500   0.5575   0.02527   0.01788  -0.1111   0.7492   1.0000
   0.750   0.5714   0.02542   0.01794  -0.1083   0.7374   1.0000
   1.000   0.6132   0.02464   0.01701  -0.1099   0.7321   1.0000
   1.250   0.6310   0.02469   0.01698  -0.1078   0.7210   1.0000
   1.500   0.6694   0.02404   0.01619  -0.1089   0.7146   1.0000
   1.750   0.6880   0.02407   0.01616  -0.1068   0.7034   1.0000
   2.000   0.7263   0.02343   0.01538  -0.1079   0.6965   1.0000
   2.250   0.7424   0.02357   0.01547  -0.1056   0.6845   1.0000
   2.500   0.7827   0.02292   0.01469  -0.1071   0.6779   1.0000
   2.750   0.7947   0.02324   0.01497  -0.1041   0.6653   1.0000
   3.000   0.8376   0.02257   0.01416  -0.1061   0.6592   1.0000
   3.250   0.8471   0.02296   0.01454  -0.1027   0.6463   1.0000
   3.500   0.8721   0.02290   0.01441  -0.1019   0.6369   1.0000
   3.750   0.8986   0.02279   0.01422  -0.1013   0.6276   1.0000
   4.000   0.9152   0.02306   0.01447  -0.0992   0.6174   1.0000
   4.250   0.9472   0.02287   0.01418  -0.0997   0.6098   1.0000
   4.500   0.9605   0.02332   0.01463  -0.0971   0.5998   1.0000
   4.750   0.9944   0.02313   0.01433  -0.0979   0.5926   1.0000
   5.000   1.0057   0.02367   0.01488  -0.0950   0.5830   1.0000
   5.250   1.0388   0.02359   0.01471  -0.0957   0.5761   1.0000
   5.500   1.0508   0.02422   0.01537  -0.0931   0.5677   1.0000
   5.750   1.0771   0.02444   0.01554  -0.0928   0.5609   1.0000
   6.000   1.1006   0.02485   0.01592  -0.0921   0.5544   1.0000
   6.250   1.1132   0.02549   0.01661  -0.0896   0.5468   1.0000
   6.500   1.1519   0.02551   0.01652  -0.0914   0.5412   1.0000
   6.750   1.1531   0.02655   0.01767  -0.0872   0.5339   1.0000
   7.000   1.1757   0.02702   0.01816  -0.0864   0.5278   1.0000
   7.250   1.2081   0.02727   0.01834  -0.0873   0.5218   1.0000
   7.500   1.2094   0.02821   0.01939  -0.0830   0.5138   1.0000
   7.750   1.2583   0.02785   0.01885  -0.0863   0.5061   1.0000
   8.000   1.2491   0.02902   0.02021  -0.0804   0.4981   1.0000
   8.250   1.2857   0.02898   0.02008  -0.0817   0.4907   1.0000
   8.500   1.2902   0.02989   0.02111  -0.0781   0.4833   1.0000
   8.750   1.3114   0.03024   0.02147  -0.0771   0.4756   1.0000
   9.000   1.3381   0.03066   0.02187  -0.0770   0.4691   1.0000
   9.250   1.3374   0.03172   0.02309  -0.0728   0.4623   1.0000
   9.500   1.3754   0.03176   0.02307  -0.0744   0.4558   1.0000
   9.750   1.3762   0.03287   0.02433  -0.0705   0.4493   1.0000
  10.000   1.3866   0.03359   0.02515  -0.0680   0.4424   1.0000
  10.250   1.4293   0.03357   0.02505  -0.0704   0.4357   1.0000
  10.500   1.4093   0.03509   0.02681  -0.0635   0.4289   1.0000
  10.750   1.4492   0.03490   0.02657  -0.0652   0.4212   1.0000
  11.000   1.4405   0.03612   0.02794  -0.0600   0.4144   1.0000
  11.250   1.4508   0.03665   0.02854  -0.0575   0.4065   1.0000
  11.500   1.4694   0.03706   0.02899  -0.0563   0.3986   1.0000
  11.750   1.4622   0.03820   0.03026  -0.0517   0.3906   1.0000
  12.000   1.4891   0.03822   0.03028  -0.0515   0.3819   1.0000
  12.250   1.4770   0.03959   0.03179  -0.0466   0.3733   1.0000
  12.500   1.4923   0.03993   0.03216  -0.0450   0.3637   1.0000
  12.750   1.5049   0.04021   0.03246  -0.0431   0.3533   1.0000
  13.000   1.4872   0.04215   0.03455  -0.0384   0.3436   1.0000
  13.250   1.5103   0.04195   0.03426  -0.0375   0.3320   1.0000
  13.500   1.4997   0.04358   0.03599  -0.0338   0.3213   1.0000
  13.750   1.4889   0.04553   0.03803  -0.0306   0.3107   1.0000
  14.000   1.5032   0.04583   0.03826  -0.0292   0.2993   1.0000
  14.250   1.4940   0.04780   0.04030  -0.0264   0.2888   1.0000
  14.500   1.4826   0.05023   0.04282  -0.0239   0.2792   1.0000
  14.750   1.4955   0.05065   0.04312  -0.0227   0.2689   1.0000
  15.000   1.4743   0.05421   0.04686  -0.0202   0.2604   1.0000
  15.250   1.4779   0.05568   0.04830  -0.0190   0.2516   1.0000
  15.500   1.4693   0.05847   0.05120  -0.0175   0.2437   1.0000
  15.750   1.4709   0.06044   0.05319  -0.0165   0.2363   1.0000
  16.000   1.4629   0.06350   0.05635  -0.0155   0.2293   1.0000
  16.250   1.4682   0.06518   0.05802  -0.0148   0.2223   1.0000
  16.500   1.4545   0.06911   0.06211  -0.0141   0.2160   1.0000
  16.750   1.4665   0.07006   0.06297  -0.0135   0.2087   1.0000
  17.000   1.4465   0.07501   0.06813  -0.0133   0.2033   1.0000
  17.250   1.4641   0.07520   0.06817  -0.0127   0.1953   1.0000
  17.500   1.4391   0.08105   0.07430  -0.0131   0.1906   1.0000
  17.750   1.4436   0.08301   0.07623  -0.0129   0.1836   1.0000
  18.000   1.4359   0.08679   0.08012  -0.0131   0.1782   1.0000
  18.250   1.4236   0.09129   0.08476  -0.0138   0.1725   1.0000
  18.500   1.4301   0.09302   0.08644  -0.0137   0.1652   1.0000
  18.750   1.4080   0.09913   0.09277  -0.0151   0.1600   1.0000
  19.000   1.4136   0.10094   0.09451  -0.0153   0.1514   1.0000
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