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GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 564 AIRFOIL (goe564-il)
Reynolds number: 100,000
Max Cl/Cd: 52.55 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe564-il-100000-n5.txt
Download as CSV file: xf-goe564-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 564 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4471   0.09149   0.08635  -0.0326   1.0000   0.0365
  -8.750  -0.4527   0.08769   0.08263  -0.0335   1.0000   0.0362
  -8.500  -0.4609   0.08398   0.07899  -0.0341   1.0000   0.0361
  -8.250  -0.4732   0.08047   0.07558  -0.0344   1.0000   0.0359
  -8.000  -0.4856   0.07657   0.07177  -0.0352   1.0000   0.0357
  -7.750  -0.4953   0.07196   0.06721  -0.0370   1.0000   0.0356
  -7.500  -0.5037   0.06702   0.06227  -0.0387   1.0000   0.0356
  -7.250  -0.5096   0.06191   0.05710  -0.0400   1.0000   0.0361
  -7.000  -0.5131   0.05655   0.05161  -0.0411   1.0000   0.0370
  -6.750  -0.5154   0.05022   0.04502  -0.0419   1.0000   0.0381
  -6.500  -0.5163   0.04286   0.03716  -0.0423   1.0000   0.0393
  -6.250  -0.5118   0.03636   0.02988  -0.0418   1.0000   0.0404
  -6.000  -0.4996   0.03306   0.02615  -0.0407   1.0000   0.0422
  -5.750  -0.4827   0.03244   0.02550  -0.0396   1.0000   0.0446
  -5.500  -0.4657   0.03032   0.02302  -0.0385   1.0000   0.0467
  -5.250  -0.4473   0.02784   0.02003  -0.0375   1.0000   0.0488
  -5.000  -0.4142   0.02557   0.01704  -0.0390   0.9962   0.0525
  -4.750  -0.3821   0.02420   0.01552  -0.0404   0.9923   0.0548
  -4.500  -0.3505   0.02309   0.01419  -0.0415   0.9886   0.0572
  -4.250  -0.3177   0.02216   0.01301  -0.0427   0.9854   0.0611
  -4.000  -0.2876   0.02121   0.01178  -0.0432   0.9813   0.0648
  -3.750  -0.2559   0.02045   0.01099  -0.0442   0.9776   0.0679
  -3.500  -0.2241   0.01980   0.01025  -0.0451   0.9738   0.0723
  -3.250  -0.1942   0.01915   0.00948  -0.0456   0.9691   0.0779
  -3.000  -0.1611   0.01869   0.00902  -0.0468   0.9652   0.0868
  -2.750  -0.1314   0.01834   0.00866  -0.0473   0.9600   0.1006
  -2.500  -0.1001   0.01804   0.00834  -0.0482   0.9549   0.1180
  -2.250  -0.0653   0.01775   0.00801  -0.0497   0.9511   0.1340
  -2.000  -0.0386   0.01751   0.00778  -0.0496   0.9442   0.1497
  -1.750  -0.0060   0.01723   0.00760  -0.0508   0.9393   0.1734
  -1.500   0.0262   0.01695   0.00737  -0.0518   0.9342   0.1941
  -1.250   0.0548   0.01664   0.00717  -0.0520   0.9273   0.2164
  -1.000   0.0904   0.01622   0.00696  -0.0537   0.9230   0.2626
  -0.750   0.1177   0.01545   0.00689  -0.0539   0.9162   0.4415
  -0.500   0.1960   0.01420   0.00703  -0.0633   0.9217   1.0000
  -0.250   0.2229   0.01422   0.00692  -0.0630   0.9121   1.0000
   0.000   0.2628   0.01416   0.00674  -0.0653   0.9073   1.0000
   0.250   0.2912   0.01415   0.00664  -0.0653   0.8973   1.0000
   0.500   0.3292   0.01402   0.00644  -0.0671   0.8894   1.0000
   0.750   0.3672   0.01380   0.00616  -0.0686   0.8788   1.0000
   1.000   0.4020   0.01357   0.00588  -0.0694   0.8647   1.0000
   1.250   0.4372   0.01333   0.00558  -0.0702   0.8492   1.0000
   1.500   0.4656   0.01319   0.00541  -0.0697   0.8296   1.0000
   1.750   0.4961   0.01307   0.00525  -0.0697   0.8104   1.0000
   2.000   0.5260   0.01301   0.00517  -0.0696   0.7925   1.0000
   2.250   0.5542   0.01301   0.00516  -0.0693   0.7748   1.0000
   2.500   0.5789   0.01305   0.00521  -0.0683   0.7531   1.0000
   2.750   0.6057   0.01307   0.00521  -0.0676   0.7275   1.0000
   3.000   0.6328   0.01309   0.00518  -0.0670   0.6967   1.0000
   3.250   0.6611   0.01317   0.00514  -0.0665   0.6632   1.0000
   3.500   0.6878   0.01335   0.00517  -0.0657   0.6261   1.0000
   3.750   0.7116   0.01363   0.00532  -0.0646   0.5881   1.0000
   4.000   0.7336   0.01396   0.00554  -0.0631   0.5460   1.0000
   4.250   0.7540   0.01435   0.00576  -0.0614   0.4937   1.0000
   4.500   0.7724   0.01488   0.00603  -0.0594   0.4330   1.0000
   4.750   0.7898   0.01555   0.00638  -0.0574   0.3748   1.0000
   5.000   0.8081   0.01620   0.00681  -0.0557   0.3307   1.0000
   5.250   0.8274   0.01682   0.00728  -0.0541   0.2983   1.0000
   5.500   0.8473   0.01742   0.00781  -0.0527   0.2752   1.0000
   5.750   0.8677   0.01800   0.00835  -0.0514   0.2582   1.0000
   6.250   0.9087   0.01915   0.00950  -0.0489   0.2283   1.0000
   6.500   0.9290   0.01973   0.01013  -0.0476   0.2114   1.0000
   6.750   0.9492   0.02030   0.01074  -0.0464   0.1939   1.0000
   7.000   0.9693   0.02087   0.01138  -0.0451   0.1780   1.0000
   7.250   0.9890   0.02144   0.01199  -0.0438   0.1591   1.0000
   7.500   1.0087   0.02200   0.01258  -0.0426   0.1365   1.0000
   7.750   1.0274   0.02267   0.01325  -0.0412   0.1114   1.0000
   8.000   1.0429   0.02369   0.01408  -0.0395   0.0887   1.0000
   8.250   1.0581   0.02487   0.01527  -0.0376   0.0691   1.0000
   8.500   1.0733   0.02603   0.01645  -0.0358   0.0540   1.0000
   8.750   1.0876   0.02722   0.01763  -0.0339   0.0454   1.0000
   9.000   1.0996   0.02856   0.01899  -0.0317   0.0402   1.0000
   9.250   1.1106   0.02992   0.02049  -0.0293   0.0367   1.0000
   9.500   1.1175   0.03148   0.02215  -0.0265   0.0340   1.0000
   9.750   1.1254   0.03301   0.02384  -0.0239   0.0314   1.0000
  10.000   1.1337   0.03455   0.02556  -0.0213   0.0295   1.0000
  10.250   1.1411   0.03625   0.02741  -0.0188   0.0281   1.0000
  10.500   1.1475   0.03807   0.02935  -0.0165   0.0268   1.0000
  10.750   1.1526   0.04014   0.03151  -0.0142   0.0257   1.0000
  11.000   1.1576   0.04257   0.03409  -0.0122   0.0245   1.0000
  11.250   1.1626   0.04461   0.03643  -0.0101   0.0236   1.0000
  11.500   1.1646   0.04698   0.03908  -0.0080   0.0225   1.0000
  11.750   1.1649   0.04963   0.04200  -0.0061   0.0220   1.0000
  12.000   1.1619   0.05256   0.04520  -0.0044   0.0215   1.0000
  12.250   1.1558   0.05579   0.04870  -0.0030   0.0211   1.0000
  12.500   1.1470   0.05939   0.05256  -0.0021   0.0209   1.0000
  12.750   1.1352   0.06344   0.05687  -0.0018   0.0207   1.0000
  13.000   1.1216   0.06793   0.06161  -0.0022   0.0206   1.0000
  13.250   1.1048   0.07318   0.06711  -0.0037   0.0205   1.0000
  13.500   1.0855   0.07934   0.07350  -0.0064   0.0205   1.0000
  13.750   1.0638   0.08656   0.08095  -0.0103   0.0207   1.0000
  14.000   1.0385   0.09536   0.08997  -0.0159   0.0210   1.0000
  14.250   1.0092   0.10636   0.10116  -0.0233   0.0214   1.0000
  14.500   0.9760   0.11982   0.11476  -0.0321   0.0221   1.0000
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