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GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 436 AIRFOIL (goe436-il)
Reynolds number: 200,000
Max Cl/Cd: 69.09 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe436-il-200000-n5.txt
Download as CSV file: xf-goe436-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 436 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3745   0.09220   0.08844  -0.0390   1.0000   0.0340
  -9.500  -0.3889   0.08699   0.08328  -0.0410   1.0000   0.0351
  -9.250  -0.4146   0.08062   0.07701  -0.0433   1.0000   0.0360
  -9.000  -0.4175   0.07896   0.07541  -0.0422   1.0000   0.0363
  -8.750  -0.4318   0.07668   0.07320  -0.0407   1.0000   0.0365
  -8.500  -0.4394   0.07413   0.07070  -0.0413   0.9979   0.0369
  -8.250  -0.4219   0.06854   0.06506  -0.0498   0.9900   0.0376
  -8.000  -0.4055   0.06232   0.05875  -0.0585   0.9827   0.0389
  -7.500  -0.4048   0.03638   0.03151  -0.0774   0.9605   0.0431
  -7.250  -0.3805   0.03554   0.03060  -0.0778   0.9542   0.0438
  -7.000  -0.3539   0.03404   0.02897  -0.0790   0.9494   0.0447
  -6.750  -0.3270   0.03116   0.02576  -0.0808   0.9459   0.0458
  -6.500  -0.3078   0.02850   0.02272  -0.0805   0.9379   0.0469
  -6.250  -0.2813   0.02593   0.01969  -0.0813   0.9324   0.0488
  -6.000  -0.2561   0.02384   0.01712  -0.0814   0.9251   0.0500
  -5.750  -0.2284   0.02218   0.01512  -0.0818   0.9175   0.0509
  -5.500  -0.1995   0.02097   0.01378  -0.0822   0.9098   0.0517
  -5.250  -0.1698   0.02016   0.01287  -0.0827   0.9013   0.0527
  -5.000  -0.1409   0.01950   0.01211  -0.0829   0.8924   0.0540
  -4.750  -0.1098   0.01876   0.01122  -0.0835   0.8843   0.0556
  -4.500  -0.0819   0.01799   0.01029  -0.0834   0.8739   0.0568
  -4.250  -0.0520   0.01722   0.00934  -0.0836   0.8637   0.0582
  -4.000  -0.0225   0.01656   0.00852  -0.0837   0.8532   0.0593
  -3.750   0.0050   0.01606   0.00787  -0.0834   0.8421   0.0604
  -3.500   0.0326   0.01537   0.00714  -0.0832   0.8323   0.0622
  -3.250   0.0603   0.01497   0.00671  -0.0831   0.8217   0.0641
  -3.000   0.0866   0.01461   0.00630  -0.0826   0.8102   0.0658
  -2.750   0.1133   0.01424   0.00587  -0.0821   0.7985   0.0676
  -2.500   0.1400   0.01391   0.00546  -0.0817   0.7866   0.0694
  -2.250   0.1659   0.01364   0.00512  -0.0810   0.7732   0.0715
  -2.000   0.1911   0.01334   0.00478  -0.0803   0.7583   0.0738
  -1.750   0.2161   0.01303   0.00447  -0.0796   0.7423   0.0767
  -1.500   0.2414   0.01282   0.00421  -0.0789   0.7249   0.0793
  -1.250   0.2666   0.01265   0.00397  -0.0781   0.7060   0.0824
  -1.000   0.2918   0.01253   0.00374  -0.0773   0.6854   0.0857
  -0.750   0.3162   0.01238   0.00352  -0.0764   0.6642   0.0907
  -0.500   0.3408   0.01232   0.00337  -0.0756   0.6435   0.0965
  -0.250   0.3653   0.01228   0.00324  -0.0747   0.6236   0.1033
   0.000   0.3898   0.01224   0.00315  -0.0739   0.6047   0.1147
   0.250   0.4137   0.01217   0.00311  -0.0730   0.5855   0.1406
   0.500   0.4360   0.01191   0.00308  -0.0720   0.5654   0.2344
   1.000   0.5457   0.01042   0.00337  -0.0830   0.5074   0.9986
   1.250   0.5687   0.01063   0.00339  -0.0820   0.4873   1.0000
   1.500   0.5899   0.01084   0.00344  -0.0806   0.4709   1.0000
   1.750   0.6114   0.01105   0.00351  -0.0793   0.4568   1.0000
   2.000   0.6332   0.01126   0.00361  -0.0780   0.4446   1.0000
   2.250   0.6552   0.01149   0.00372  -0.0768   0.4344   1.0000
   2.500   0.6775   0.01171   0.00384  -0.0757   0.4251   1.0000
   2.750   0.7002   0.01192   0.00398  -0.0746   0.4175   1.0000
   3.000   0.7231   0.01214   0.00414  -0.0736   0.4104   1.0000
   3.250   0.7460   0.01237   0.00430  -0.0726   0.4044   1.0000
   3.500   0.7695   0.01257   0.00448  -0.0716   0.3978   1.0000
   3.750   0.7925   0.01282   0.00467  -0.0707   0.3919   1.0000
   4.000   0.8161   0.01304   0.00487  -0.0698   0.3865   1.0000
   4.250   0.8399   0.01326   0.00507  -0.0690   0.3809   1.0000
   4.500   0.8628   0.01353   0.00529  -0.0680   0.3747   1.0000
   4.750   0.8863   0.01373   0.00551  -0.0672   0.3673   1.0000
   5.000   0.9089   0.01398   0.00571  -0.0662   0.3595   1.0000
   5.250   0.9318   0.01419   0.00593  -0.0652   0.3507   1.0000
   5.500   0.9537   0.01445   0.00614  -0.0641   0.3422   1.0000
   5.750   0.9769   0.01465   0.00638  -0.0633   0.3341   1.0000
   6.000   0.9992   0.01491   0.00663  -0.0622   0.3272   1.0000
   6.250   1.0223   0.01514   0.00690  -0.0614   0.3211   1.0000
   6.500   1.0449   0.01538   0.00718  -0.0604   0.3145   1.0000
   6.750   1.0670   0.01565   0.00746  -0.0594   0.3081   1.0000
   7.000   1.0896   0.01589   0.00777  -0.0585   0.3010   1.0000
   7.250   1.1108   0.01619   0.00807  -0.0574   0.2946   1.0000
   7.500   1.1333   0.01643   0.00840  -0.0564   0.2873   1.0000
   7.750   1.1539   0.01674   0.00873  -0.0552   0.2798   1.0000
   8.000   1.1752   0.01701   0.00908  -0.0541   0.2704   1.0000
   8.250   1.1951   0.01734   0.00944  -0.0528   0.2621   1.0000
   8.500   1.2149   0.01766   0.00981  -0.0515   0.2517   1.0000
   8.750   1.2338   0.01802   0.01022  -0.0501   0.2396   1.0000
   9.000   1.2513   0.01843   0.01065  -0.0484   0.2257   1.0000
   9.250   1.2665   0.01890   0.01111  -0.0464   0.2097   1.0000
   9.500   1.2779   0.01950   0.01165  -0.0438   0.1902   1.0000
   9.750   1.2862   0.02029   0.01234  -0.0409   0.1674   1.0000
  10.000   1.2941   0.02118   0.01315  -0.0381   0.1484   1.0000
  10.250   1.3011   0.02216   0.01407  -0.0353   0.1297   1.0000
  10.500   1.3072   0.02324   0.01508  -0.0326   0.1126   1.0000
  10.750   1.3127   0.02438   0.01618  -0.0300   0.0961   1.0000
  11.000   1.3174   0.02561   0.01736  -0.0275   0.0798   1.0000
  11.250   1.3204   0.02701   0.01869  -0.0250   0.0709   1.0000
  11.500   1.3234   0.02845   0.02016  -0.0227   0.0658   1.0000
  11.750   1.3267   0.02995   0.02171  -0.0207   0.0625   1.0000
  12.000   1.3315   0.03142   0.02329  -0.0189   0.0597   1.0000
  12.250   1.3339   0.03315   0.02510  -0.0173   0.0572   1.0000
  12.500   1.3338   0.03517   0.02721  -0.0157   0.0550   1.0000
  12.750   1.3305   0.03760   0.02972  -0.0144   0.0529   1.0000
  13.000   1.3353   0.03943   0.03169  -0.0135   0.0512   1.0000
  13.250   1.3379   0.04155   0.03395  -0.0128   0.0487   1.0000
  13.500   1.3372   0.04411   0.03664  -0.0123   0.0466   1.0000
  13.750   1.3328   0.04721   0.03984  -0.0121   0.0446   1.0000
  14.000   1.3289   0.05042   0.04315  -0.0121   0.0429   1.0000
  14.250   1.3308   0.05307   0.04597  -0.0122   0.0404   1.0000
  14.500   1.3287   0.05631   0.04932  -0.0126   0.0377   1.0000
  14.750   1.3233   0.06009   0.05318  -0.0133   0.0357   1.0000
  15.000   1.3214   0.06352   0.05677  -0.0140   0.0332   1.0000
  15.250   1.3168   0.06745   0.06078  -0.0150   0.0306   1.0000
  15.500   1.3111   0.07163   0.06507  -0.0162   0.0286   1.0000
  15.750   1.3051   0.07594   0.06949  -0.0175   0.0270   1.0000
  16.000   1.2973   0.08062   0.07424  -0.0191   0.0254   1.0000
  16.250   1.2895   0.08537   0.07908  -0.0208   0.0244   1.0000
  16.500   1.2820   0.09012   0.08394  -0.0224   0.0232   1.0000
  16.750   1.2743   0.09498   0.08889  -0.0242   0.0223   1.0000
  17.000   1.2665   0.09992   0.09392  -0.0262   0.0216   1.0000
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