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GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 8K AIRFOIL (goe08k-il)
Reynolds number: 200,000
Max Cl/Cd: 43.5 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe08k-il-200000-n5.txt
Download as CSV file: xf-goe08k-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 8K 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0392   0.10531   0.10105  -0.1433   0.9017   0.0190
 -10.750  -0.0381   0.10177   0.09752  -0.1443   0.8994   0.0186
 -10.500  -0.0357   0.09782   0.09358  -0.1462   0.8977   0.0189
 -10.250  -0.0322   0.09370   0.08946  -0.1486   0.8964   0.0186
 -10.000  -0.0300   0.08907   0.08483  -0.1515   0.8953   0.0196
  -9.750  -0.0479   0.08770   0.08351  -0.1472   0.8878   0.0193
  -9.500  -0.0550   0.08378   0.07962  -0.1478   0.8843   0.0191
  -9.250  -0.0599   0.07904   0.07489  -0.1503   0.8822   0.0199
  -9.000  -0.0664   0.07370   0.06956  -0.1537   0.8804   0.0200
  -8.750  -0.1025   0.07261   0.06856  -0.1472   0.8700   0.0201
  -8.500  -0.1190   0.06824   0.06419  -0.1485   0.8668   0.0191
  -8.250  -0.1568   0.06726   0.06324  -0.1410   0.8569   0.0196
  -8.000  -0.1762   0.06180   0.05770  -0.1404   0.8526   0.0198
  -7.750  -0.2061   0.05859   0.05441  -0.1346   0.8447   0.0199
  -7.500  -0.2296   0.05318   0.04882  -0.1306   0.8389   0.0199
  -7.250  -0.2657   0.04200   0.03694  -0.1251   0.8360   0.0205
  -7.000  -0.3214   0.03623   0.03045  -0.1113   0.8248   0.0210
  -6.750  -0.3122   0.03381   0.02766  -0.1087   0.8232   0.0216
  -6.500  -0.2778   0.03544   0.02950  -0.1103   0.8223   0.0226
  -6.250  -0.2953   0.03362   0.02730  -0.1022   0.8151   0.0227
  -6.000  -0.2824   0.03329   0.02684  -0.0999   0.8119   0.0239
  -5.750  -0.2724   0.03066   0.02363  -0.0965   0.8100   0.0261
  -5.500  -0.2521   0.02960   0.02233  -0.0953   0.8087   0.0277
  -5.250  -0.2262   0.02955   0.02224  -0.0952   0.8077   0.0291
  -4.750  -0.2160   0.02931   0.02164  -0.0869   0.7980   0.0327
  -4.500  -0.1968   0.02854   0.02061  -0.0854   0.7962   0.0355
  -4.250  -0.1737   0.02859   0.02065  -0.0848   0.7948   0.0376
  -4.000  -0.1497   0.02810   0.01996  -0.0841   0.7938   0.0407
  -3.750  -0.1246   0.02761   0.01914  -0.0835   0.7930   0.0444
  -3.500  -0.1294   0.02796   0.01939  -0.0776   0.7859   0.0454
  -3.250  -0.1130   0.02785   0.01929  -0.0759   0.7831   0.0476
  -3.000  -0.0910   0.02761   0.01896  -0.0750   0.7815   0.0507
  -2.750  -0.0670   0.02727   0.01847  -0.0744   0.7803   0.0534
  -2.500  -0.0416   0.02712   0.01813  -0.0739   0.7793   0.0560
  -2.250  -0.0151   0.02630   0.01729  -0.0740   0.7786   0.0587
  -1.750  -0.0018   0.02702   0.01798  -0.0668   0.7690   0.0623
  -1.500   0.0205   0.02685   0.01774  -0.0660   0.7673   0.0639
  -1.250   0.0449   0.02661   0.01744  -0.0656   0.7660   0.0654
  -1.000   0.0705   0.02641   0.01718  -0.0653   0.7650   0.0675
  -0.750   0.0971   0.02623   0.01694  -0.0653   0.7641   0.0688
  -0.500   0.1242   0.02578   0.01649  -0.0653   0.7634   0.0706
  -0.250   0.1454   0.02568   0.01640  -0.0643   0.7616   0.0719
   1.250   0.2357   0.02753   0.01813  -0.0526   0.7392   0.0818
   1.500   0.2635   0.02736   0.01791  -0.0528   0.7372   0.0833
   1.750   0.2935   0.02711   0.01766  -0.0533   0.7358   0.0870
   2.000   0.3237   0.02689   0.01747  -0.0540   0.7347   0.0953
   2.500   0.6402   0.02520   0.01837  -0.1133   0.7489   1.0000
   2.750   0.6705   0.02493   0.01806  -0.1139   0.7482   1.0000
   3.000   0.7010   0.02471   0.01782  -0.1146   0.7476   1.0000
   3.500   0.7125   0.02655   0.01967  -0.1076   0.7347   1.0000
   3.750   0.7139   0.02780   0.02092  -0.1036   0.7270   1.0000
   4.000   0.7335   0.02805   0.02118  -0.1024   0.7231   1.0000
   4.250   0.7608   0.02789   0.02102  -0.1025   0.7214   1.0000
   4.500   0.7893   0.02769   0.02084  -0.1028   0.7201   1.0000
   4.750   0.8198   0.02735   0.02051  -0.1034   0.7191   1.0000
   5.000   0.8522   0.02691   0.02010  -0.1042   0.7182   1.0000
   5.250   0.8842   0.02655   0.01978  -0.1051   0.7175   1.0000
   5.750   0.9017   0.02808   0.02141  -0.0994   0.7039   1.0000
   6.000   0.9238   0.02817   0.02155  -0.0987   0.7004   1.0000
   7.000   0.9927   0.02906   0.02269  -0.0923   0.6749   1.0000
   7.250   1.0227   0.02842   0.02211  -0.0925   0.6698   1.0000
   8.250   1.0679   0.03059   0.02454  -0.0827   0.6186   1.0000
   8.500   1.0889   0.03056   0.02456  -0.0817   0.6037   1.0000
   8.750   1.1294   0.02909   0.02308  -0.0831   0.5806   1.0000
   9.000   1.1767   0.02705   0.02060  -0.0851   0.5206   1.0000
   9.250   1.1853   0.02774   0.02105  -0.0822   0.4798   1.0000
   9.500   1.1844   0.02906   0.02214  -0.0780   0.4378   1.0000
   9.750   1.1754   0.03094   0.02376  -0.0728   0.3861   1.0000
  10.000   1.1616   0.03326   0.02572  -0.0673   0.3284   1.0000
  10.250   1.1517   0.03548   0.02768  -0.0627   0.2775   1.0000
  10.500   1.1443   0.03767   0.02961  -0.0587   0.2325   1.0000
  10.750   1.1402   0.03973   0.03144  -0.0552   0.1925   1.0000
  11.000   1.1385   0.04167   0.03318  -0.0521   0.1509   1.0000
  11.250   1.1327   0.04399   0.03516  -0.0488   0.0981   1.0000
  11.500   1.1329   0.04592   0.03694  -0.0462   0.0728   1.0000
  11.750   1.1369   0.04761   0.03857  -0.0440   0.0543   1.0000
  12.000   1.1409   0.04931   0.04022  -0.0419   0.0393   1.0000
  12.250   1.1462   0.05096   0.04187  -0.0400   0.0323   1.0000
  12.500   1.1529   0.05252   0.04349  -0.0383   0.0285   1.0000
  12.750   1.1569   0.05436   0.04539  -0.0364   0.0260   1.0000
  13.000   1.1599   0.05633   0.04745  -0.0345   0.0239   1.0000
  13.250   1.1663   0.05799   0.04923  -0.0330   0.0226   1.0000
  13.500   1.1707   0.05986   0.05120  -0.0314   0.0214   1.0000
  13.750   1.1745   0.06181   0.05326  -0.0299   0.0201   1.0000
  14.000   1.1755   0.06406   0.05558  -0.0282   0.0190   1.0000
  14.250   1.1781   0.06620   0.05782  -0.0267   0.0181   1.0000
  14.500   1.1833   0.06811   0.05983  -0.0255   0.0168   1.0000
  14.750   1.1864   0.07025   0.06206  -0.0242   0.0159   1.0000
  15.000   1.1892   0.07243   0.06433  -0.0230   0.0156   1.0000
  15.250   1.1908   0.07474   0.06669  -0.0218   0.0151   1.0000
  15.500   1.1923   0.07709   0.06912  -0.0206   0.0146   1.0000
  15.750   1.1962   0.07920   0.07138  -0.0195   0.0142   1.0000
  16.000   1.2005   0.08130   0.07361  -0.0185   0.0136   1.0000
  16.250   1.2039   0.08351   0.07593  -0.0175   0.0129   1.0000
  16.500   1.2088   0.08553   0.07806  -0.0167   0.0129   1.0000
  16.750   1.2119   0.08782   0.08044  -0.0161   0.0124   1.0000
  17.000   1.2143   0.09019   0.08286  -0.0154   0.0119   1.0000
  17.250   1.2169   0.09248   0.08520  -0.0148   0.0115   1.0000
  17.500   1.2197   0.09493   0.08785  -0.0142   0.0111   1.0000
  17.750   1.2220   0.09740   0.09049  -0.0137   0.0109   1.0000
  18.000   1.2244   0.09987   0.09313  -0.0131   0.0107   1.0000
  18.250   1.2236   0.10284   0.09627  -0.0129   0.0103   1.0000
  18.500   1.2234   0.10573   0.09936  -0.0127   0.0102   1.0000
  18.750   1.2207   0.10904   0.10283  -0.0128   0.0099   1.0000
  19.000   1.2178   0.11243   0.10638  -0.0130   0.0098   1.0000
  19.250   1.2139   0.11606   0.11020  -0.0135   0.0097   1.0000
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