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GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 383 AIRFOIL (goe383-il)
Reynolds number: 100,000
Max Cl/Cd: 40.48 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe383-il-100000-n5.txt
Download as CSV file: xf-goe383-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 383 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1824   0.09934   0.09363  -0.0840   0.9007   0.0564
 -11.500  -0.1954   0.09251   0.08677  -0.0872   0.8872   0.0563
 -11.250  -0.2976   0.06734   0.06129  -0.1049   0.8779   0.0550
 -11.000  -0.3728   0.05563   0.04904  -0.1132   0.8602   0.0543
 -10.750  -0.4010   0.05139   0.04444  -0.1129   0.8449   0.0542
 -10.500  -0.4203   0.04862   0.04137  -0.1105   0.8303   0.0543
 -10.250  -0.4286   0.04609   0.03850  -0.1084   0.8198   0.0544
 -10.000  -0.4299   0.04382   0.03591  -0.1065   0.8089   0.0546
  -9.750  -0.4254   0.04169   0.03343  -0.1048   0.8012   0.0548
  -9.500  -0.4174   0.03986   0.03132  -0.1033   0.7917   0.0551
  -9.250  -0.4059   0.03815   0.02929  -0.1019   0.7841   0.0554
  -9.000  -0.3916   0.03657   0.02739  -0.1006   0.7776   0.0558
  -8.750  -0.3758   0.03520   0.02575  -0.0995   0.7693   0.0562
  -8.500  -0.3578   0.03391   0.02417  -0.0984   0.7626   0.0567
  -8.250  -0.3360   0.03276   0.02287  -0.0977   0.7575   0.0572
  -8.000  -0.3143   0.03189   0.02198  -0.0972   0.7508   0.0579
  -7.750  -0.2922   0.03106   0.02108  -0.0966   0.7446   0.0588
  -7.500  -0.2694   0.03022   0.02012  -0.0960   0.7393   0.0599
  -7.250  -0.2458   0.02939   0.01911  -0.0954   0.7346   0.0610
  -7.000  -0.2233   0.02867   0.01827  -0.0947   0.7284   0.0620
  -6.750  -0.1997   0.02794   0.01750  -0.0941   0.7225   0.0629
  -6.500  -0.1756   0.02722   0.01675  -0.0935   0.7169   0.0638
  -6.250  -0.1521   0.02660   0.01608  -0.0929   0.7109   0.0649
  -6.000  -0.1297   0.02605   0.01551  -0.0920   0.7037   0.0661
  -5.750  -0.1060   0.02549   0.01485  -0.0913   0.6978   0.0675
  -5.500  -0.0819   0.02494   0.01424  -0.0906   0.6933   0.0691
  -5.250  -0.0597   0.02452   0.01386  -0.0898   0.6879   0.0713
  -5.000  -0.0371   0.02415   0.01345  -0.0890   0.6823   0.0739
  -4.750  -0.0138   0.02373   0.01303  -0.0883   0.6773   0.0765
  -4.500   0.0108   0.02333   0.01257  -0.0877   0.6730   0.0799
  -4.250   0.0350   0.02297   0.01219  -0.0871   0.6687   0.0837
  -4.000   0.0573   0.02272   0.01199  -0.0863   0.6632   0.0893
  -3.750   0.0807   0.02240   0.01175  -0.0856   0.6580   0.0988
  -3.500   0.1053   0.02203   0.01143  -0.0850   0.6534   0.1168
  -3.250   0.1308   0.02161   0.01108  -0.0845   0.6493   0.1464
  -3.000   0.1529   0.02132   0.01097  -0.0837   0.6442   0.1808
  -2.750   0.1746   0.02104   0.01095  -0.0829   0.6385   0.2249
  -2.500   0.1984   0.02079   0.01087  -0.0822   0.6336   0.2776
  -2.250   0.2233   0.02048   0.01072  -0.0817   0.6293   0.3319
  -2.000   0.2482   0.02015   0.01058  -0.0811   0.6254   0.3915
  -1.750   0.2668   0.01999   0.01079  -0.0796   0.6191   0.4598
  -1.500   0.2875   0.01976   0.01095  -0.0781   0.6134   0.5440
  -1.250   0.3109   0.01962   0.01107  -0.0766   0.6086   0.6272
  -1.000   0.3373   0.01958   0.01106  -0.0757   0.6045   0.6862
  -0.750   0.3594   0.01973   0.01130  -0.0743   0.5990   0.7239
  -0.500   0.3824   0.01988   0.01151  -0.0731   0.5929   0.7564
  -0.250   0.4080   0.01995   0.01157  -0.0721   0.5877   0.7904
   0.000   0.4377   0.02000   0.01158  -0.0716   0.5833   0.8230
   0.250   0.4634   0.02023   0.01183  -0.0708   0.5774   0.8532
   0.500   0.4905   0.02048   0.01208  -0.0703   0.5708   0.8794
   0.750   0.5245   0.02061   0.01214  -0.0712   0.5655   0.9005
   1.000   0.5626   0.02069   0.01207  -0.0728   0.5614   0.9166
   1.250   0.5929   0.02100   0.01239  -0.0736   0.5547   0.9329
   1.500   0.6276   0.02122   0.01255  -0.0752   0.5483   0.9484
   1.750   0.6706   0.02130   0.01251  -0.0780   0.5432   0.9634
   2.000   0.7190   0.02152   0.01265  -0.0823   0.5374   0.9766
   2.250   0.7639   0.02182   0.01293  -0.0862   0.5306   0.9893
   2.500   0.8107   0.02191   0.01292  -0.0903   0.5252   0.9994
   2.750   0.8303   0.02190   0.01278  -0.0891   0.5214   1.0000
   3.000   0.8330   0.02230   0.01324  -0.0853   0.5148   1.0000
   3.250   0.8444   0.02251   0.01340  -0.0827   0.5095   1.0000
   3.500   0.8620   0.02260   0.01340  -0.0810   0.5054   1.0000
   3.750   0.8770   0.02282   0.01356  -0.0790   0.5009   1.0000
   4.000   0.8848   0.02326   0.01400  -0.0759   0.4950   1.0000
   4.250   0.9013   0.02348   0.01416  -0.0741   0.4901   1.0000
   4.500   0.9241   0.02357   0.01415  -0.0732   0.4863   1.0000
   4.750   0.9359   0.02403   0.01461  -0.0708   0.4810   1.0000
   5.000   0.9487   0.02445   0.01503  -0.0686   0.4754   1.0000
   5.250   0.9700   0.02462   0.01512  -0.0676   0.4706   1.0000
   5.500   0.9927   0.02478   0.01519  -0.0669   0.4660   1.0000
   5.750   0.9984   0.02544   0.01590  -0.0637   0.4595   1.0000
   6.000   1.0155   0.02574   0.01615  -0.0622   0.4543   1.0000
   6.250   1.0436   0.02578   0.01608  -0.0622   0.4500   1.0000
   6.500   1.0473   0.02659   0.01694  -0.0590   0.4444   1.0000
   6.750   1.0586   0.02722   0.01759  -0.0569   0.4391   1.0000
   7.000   1.0805   0.02753   0.01784  -0.0562   0.4346   1.0000
   7.250   1.1089   0.02766   0.01788  -0.0564   0.4307   1.0000
   7.500   1.1073   0.02890   0.01924  -0.0531   0.4250   1.0000
   7.750   1.1200   0.02965   0.02000  -0.0515   0.4199   1.0000
   8.000   1.1435   0.02994   0.02025  -0.0511   0.4156   1.0000
   8.250   1.1662   0.03032   0.02058  -0.0507   0.4114   1.0000
   8.500   1.1620   0.03194   0.02233  -0.0477   0.4055   1.0000
   8.750   1.1747   0.03280   0.02322  -0.0464   0.4005   1.0000
   9.000   1.1998   0.03303   0.02340  -0.0463   0.3964   1.0000
   9.250   1.2116   0.03400   0.02440  -0.0450   0.3916   1.0000
   9.500   1.2040   0.03611   0.02665  -0.0423   0.3853   1.0000
   9.750   1.2187   0.03693   0.02748  -0.0415   0.3803   1.0000
  10.000   1.2485   0.03685   0.02732  -0.0416   0.3766   1.0000
  10.250   1.2312   0.03986   0.03052  -0.0388   0.3701   1.0000
  10.500   1.2304   0.04190   0.03264  -0.0373   0.3642   1.0000
  10.750   1.2536   0.04215   0.03286  -0.0370   0.3601   1.0000
  11.000   1.2534   0.04424   0.03503  -0.0357   0.3546   1.0000
  11.250   1.2321   0.04822   0.03917  -0.0338   0.3469   1.0000
  11.500   1.2542   0.04847   0.03940  -0.0335   0.3428   1.0000
  11.750   1.2445   0.05167   0.04270  -0.0323   0.3366   1.0000
  12.000   1.2234   0.05618   0.04734  -0.0312   0.3289   1.0000
  12.250   1.2491   0.05603   0.04717  -0.0309   0.3257   1.0000
  12.750   1.2093   0.06558   0.05695  -0.0296   0.3113   1.0000
  13.000   1.2402   0.06474   0.05609  -0.0293   0.3090   1.0000
  13.500   1.1978   0.07535   0.06691  -0.0289   0.2943   1.0000
  13.750   1.2345   0.07362   0.06513  -0.0285   0.2926   1.0000
  14.250   1.1858   0.08581   0.07753  -0.0291   0.2782   1.0000
  14.500   1.2232   0.08375   0.07544  -0.0285   0.2767   1.0000
  15.000   1.1514   0.10014   0.09206  -0.0307   0.2609   1.0000
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