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GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 647 AIRFOIL (goe647-il)
Reynolds number: 200,000
Max Cl/Cd: 58.99 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe647-il-200000.txt
Download as CSV file: xf-goe647-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 647 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1637   0.09050   0.08723  -0.0639   0.9730   0.0915
  -9.000  -0.1395   0.08685   0.08357  -0.0683   0.9689   0.0944
  -8.750  -0.2732   0.04853   0.04470  -0.1106   0.9397   0.0707
  -8.500  -0.3132   0.03562   0.03025  -0.1140   0.9231   0.0619
  -8.250  -0.2857   0.03384   0.02855  -0.1149   0.9149   0.0631
  -8.000  -0.2606   0.03132   0.02573  -0.1159   0.9072   0.0635
  -7.750  -0.2402   0.02902   0.02308  -0.1156   0.8975   0.0637
  -7.500  -0.2141   0.02703   0.02079  -0.1158   0.8890   0.0641
  -7.250  -0.1920   0.02555   0.01908  -0.1150   0.8781   0.0646
  -7.000  -0.1634   0.02413   0.01741  -0.1152   0.8695   0.0656
  -6.750  -0.1417   0.02311   0.01618  -0.1139   0.8570   0.0669
  -6.500  -0.1157   0.02209   0.01488  -0.1132   0.8458   0.0683
  -6.250  -0.0901   0.02119   0.01370  -0.1124   0.8334   0.0693
  -6.000  -0.0669   0.02002   0.01247  -0.1113   0.8200   0.0705
  -5.750  -0.0409   0.01924   0.01166  -0.1107   0.8088   0.0722
  -5.500  -0.0154   0.01862   0.01095  -0.1099   0.7974   0.0742
  -5.250   0.0088   0.01813   0.01035  -0.1089   0.7856   0.0768
  -5.000   0.0355   0.01744   0.00956  -0.1083   0.7757   0.0796
  -4.750   0.0582   0.01693   0.00909  -0.1071   0.7633   0.0828
  -4.500   0.0832   0.01651   0.00858  -0.1062   0.7524   0.0869
  -4.250   0.1074   0.01592   0.00798  -0.1052   0.7417   0.0921
  -4.000   0.1310   0.01559   0.00759  -0.1041   0.7299   0.0998
  -3.750   0.1549   0.01504   0.00702  -0.1031   0.7198   0.1125
  -3.500   0.1758   0.01436   0.00651  -0.1017   0.7083   0.1366
  -3.250   0.1989   0.01392   0.00632  -0.1007   0.6976   0.1940
  -3.000   0.2246   0.01380   0.00621  -0.1000   0.6871   0.2427
  -2.750   0.2486   0.01375   0.00618  -0.0990   0.6751   0.2715
  -2.500   0.2745   0.01375   0.00608  -0.0983   0.6643   0.2947
  -2.250   0.2994   0.01372   0.00601  -0.0974   0.6529   0.3147
  -2.000   0.3239   0.01370   0.00598  -0.0965   0.6413   0.3343
  -1.750   0.3494   0.01369   0.00593  -0.0958   0.6306   0.3554
  -1.500   0.3729   0.01367   0.00592  -0.0947   0.6181   0.3758
  -1.250   0.3973   0.01365   0.00589  -0.0937   0.6062   0.3951
  -1.000   0.4225   0.01365   0.00582  -0.0929   0.5950   0.4153
  -0.750   0.4455   0.01360   0.00582  -0.0917   0.5821   0.4379
  -0.500   0.4690   0.01357   0.00579  -0.0907   0.5695   0.4630
  -0.250   0.4925   0.01351   0.00573  -0.0896   0.5573   0.4910
   0.000   0.5144   0.01340   0.00569  -0.0882   0.5438   0.5257
   0.250   0.5351   0.01323   0.00569  -0.0866   0.5304   0.5710
   0.500   0.5542   0.01300   0.00572  -0.0846   0.5180   0.6477
   0.750   0.6595   0.01263   0.00589  -0.0997   0.4947   0.9814
   1.000   0.6940   0.01289   0.00594  -0.1012   0.4800   1.0000
   1.250   0.7142   0.01313   0.00598  -0.0996   0.4682   1.0000
   1.500   0.7345   0.01336   0.00606  -0.0981   0.4564   1.0000
   1.750   0.7552   0.01360   0.00619  -0.0967   0.4458   1.0000
   2.000   0.7763   0.01390   0.00629  -0.0953   0.4365   1.0000
   2.250   0.7972   0.01414   0.00647  -0.0939   0.4269   1.0000
   2.500   0.8188   0.01447   0.00660  -0.0927   0.4188   1.0000
   2.750   0.8398   0.01471   0.00681  -0.0914   0.4105   1.0000
   3.000   0.8616   0.01502   0.00698  -0.0902   0.4032   1.0000
   3.250   0.8835   0.01533   0.00722  -0.0891   0.3964   1.0000
   3.500   0.9052   0.01561   0.00744  -0.0879   0.3899   1.0000
   3.750   0.9290   0.01601   0.00767  -0.0872   0.3844   1.0000
   4.000   0.9507   0.01631   0.00797  -0.0860   0.3788   1.0000
   4.250   0.9728   0.01661   0.00824  -0.0850   0.3735   1.0000
   4.500   0.9965   0.01699   0.00850  -0.0843   0.3687   1.0000
   4.750   1.0199   0.01739   0.00885  -0.0835   0.3639   1.0000
   5.000   1.0410   0.01769   0.00917  -0.0823   0.3591   1.0000
   5.250   1.0635   0.01803   0.00946  -0.0814   0.3546   1.0000
   5.500   1.0890   0.01848   0.00979  -0.0811   0.3505   1.0000
   5.750   1.1117   0.01891   0.01023  -0.0803   0.3468   1.0000
   6.000   1.1327   0.01927   0.01063  -0.0792   0.3430   1.0000
   6.250   1.1551   0.01965   0.01101  -0.0783   0.3393   1.0000
   6.500   1.1791   0.02006   0.01137  -0.0778   0.3360   1.0000
   6.750   1.2080   0.02067   0.01186  -0.0783   0.3327   1.0000
   7.000   1.2273   0.02109   0.01238  -0.0769   0.3297   1.0000
   7.250   1.2467   0.02151   0.01286  -0.0756   0.3265   1.0000
   7.500   1.2677   0.02192   0.01330  -0.0746   0.3232   1.0000
   7.750   1.2907   0.02236   0.01371  -0.0739   0.3201   1.0000
   8.000   1.3169   0.02289   0.01419  -0.0739   0.3175   1.0000
   8.250   1.3446   0.02363   0.01489  -0.0743   0.3148   1.0000
   8.500   1.3604   0.02411   0.01552  -0.0725   0.3125   1.0000
   8.750   1.3781   0.02464   0.01615  -0.0710   0.3100   1.0000
   9.000   1.3973   0.02519   0.01676  -0.0699   0.3075   1.0000
   9.250   1.4182   0.02572   0.01732  -0.0690   0.3050   1.0000
   9.500   1.4415   0.02624   0.01784  -0.0686   0.3026   1.0000
   9.750   1.4696   0.02687   0.01843  -0.0691   0.3003   1.0000
  10.000   1.4932   0.02776   0.01935  -0.0689   0.2980   1.0000
  10.250   1.5050   0.02840   0.02015  -0.0666   0.2961   1.0000
  10.500   1.5171   0.02911   0.02100  -0.0645   0.2941   1.0000
  10.750   1.5300   0.02983   0.02183  -0.0626   0.2920   1.0000
  11.000   1.5436   0.03050   0.02259  -0.0607   0.2898   1.0000
  11.250   1.5604   0.03110   0.02324  -0.0594   0.2877   1.0000
  11.500   1.5829   0.03170   0.02386  -0.0590   0.2856   1.0000
  11.750   1.6131   0.03251   0.02464  -0.0600   0.2837   1.0000
  12.000   1.6342   0.03366   0.02587  -0.0597   0.2817   1.0000
  12.250   1.6297   0.03454   0.02695  -0.0552   0.2801   1.0000
  12.500   1.6267   0.03554   0.02812  -0.0513   0.2781   1.0000
  12.750   1.6269   0.03660   0.02933  -0.0481   0.2760   1.0000
  13.000   1.6304   0.03765   0.03050  -0.0456   0.2739   1.0000
  13.250   1.6392   0.03844   0.03137  -0.0437   0.2716   1.0000
  13.500   1.6649   0.03865   0.03153  -0.0437   0.2689   1.0000
  13.750   1.6972   0.03920   0.03201  -0.0448   0.2657   1.0000
  14.000   1.6726   0.04089   0.03396  -0.0395   0.2636   1.0000
  14.250   1.6567   0.04282   0.03608  -0.0358   0.2612   1.0000
  14.500   1.6462   0.04465   0.03808  -0.0330   0.2586   1.0000
  14.750   1.6517   0.04553   0.03900  -0.0316   0.2556   1.0000
  15.000   1.6989   0.04416   0.03745  -0.0329   0.2520   1.0000
  15.250   1.6990   0.04580   0.03919  -0.0312   0.2494   1.0000
  15.500   1.6642   0.04947   0.04315  -0.0279   0.2473   1.0000
  15.750   1.6289   0.05388   0.04780  -0.0256   0.2449   1.0000
  16.000   1.6023   0.05807   0.05217  -0.0243   0.2422   1.0000
  16.250   1.6144   0.05886   0.05300  -0.0239   0.2395   1.0000
  16.500   1.7074   0.05294   0.04673  -0.0251   0.2353   1.0000
  16.750   1.6499   0.05968   0.05382  -0.0232   0.2336   1.0000
  17.750   1.6153   0.07190   0.06645  -0.0228   0.2216   1.0000
  18.000   0.9943   0.18127   0.17633  -0.0676   0.1706   1.0000
  18.250   1.0126   0.18134   0.17644  -0.0674   0.1689   1.0000
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