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GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 701 AIRFOIL (goe701-il)
Reynolds number: 100,000
Max Cl/Cd: 53.72 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe701-il-100000-n5.txt
Download as CSV file: xf-goe701-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 701 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3322   0.11412   0.10889  -0.0429   1.0000   0.0584
 -10.500  -0.3406   0.11117   0.10600  -0.0424   1.0000   0.0585
 -10.250  -0.3580   0.10755   0.10246  -0.0424   1.0000   0.0592
 -10.000  -0.3643   0.10510   0.10008  -0.0417   0.9997   0.0602
  -9.750  -0.3381   0.10365   0.09860  -0.0430   0.9964   0.0624
  -9.500  -0.3275   0.09924   0.09417  -0.0473   0.9917   0.0631
  -9.250  -0.3183   0.09474   0.08965  -0.0519   0.9863   0.0640
  -9.000  -0.3110   0.09007   0.08496  -0.0569   0.9805   0.0657
  -8.750  -0.3082   0.08456   0.07945  -0.0628   0.9731   0.0667
  -8.500  -0.3115   0.07893   0.07381  -0.0685   0.9633   0.0671
  -8.250  -0.3199   0.07173   0.06658  -0.0761   0.9512   0.0678
  -8.000  -0.3364   0.05999   0.05464  -0.0874   0.9377   0.0692
  -7.500  -0.2989   0.05431   0.04876  -0.0924   0.9259   0.0714
  -7.250  -0.2980   0.04861   0.04279  -0.0945   0.9151   0.0726
  -7.000  -0.2937   0.04246   0.03617  -0.0965   0.9068   0.0751
  -6.750  -0.2920   0.03557   0.02837  -0.0972   0.8984   0.0781
  -6.500  -0.2650   0.03290   0.02530  -0.0987   0.8953   0.0798
  -6.250  -0.2506   0.03213   0.02445  -0.0967   0.8859   0.0809
  -6.000  -0.2202   0.03109   0.02326  -0.0977   0.8822   0.0831
  -5.750  -0.1933   0.02966   0.02152  -0.0981   0.8776   0.0861
  -5.500  -0.1754   0.02811   0.01954  -0.0968   0.8699   0.0889
  -5.250  -0.1443   0.02678   0.01795  -0.0977   0.8662   0.0912
  -5.000  -0.1151   0.02615   0.01729  -0.0981   0.8617   0.0936
  -4.750  -0.0932   0.02564   0.01666  -0.0970   0.8543   0.0968
  -4.500  -0.0612   0.02466   0.01537  -0.0978   0.8505   0.1014
  -4.250  -0.0290   0.02376   0.01433  -0.0986   0.8468   0.1050
  -4.000  -0.0090   0.02342   0.01398  -0.0972   0.8387   0.1081
  -3.750   0.0237   0.02284   0.01326  -0.0980   0.8346   0.1139
  -3.500   0.0591   0.02212   0.01238  -0.0992   0.8316   0.1200
  -3.250   0.0771   0.02193   0.01222  -0.0974   0.8226   0.1242
  -3.000   0.1099   0.02144   0.01161  -0.0981   0.8183   0.1311
  -2.750   0.1425   0.02100   0.01113  -0.0989   0.8141   0.1378
  -2.500   0.1634   0.02087   0.01099  -0.0975   0.8058   0.1437
  -2.250   0.1965   0.02047   0.01048  -0.0982   0.8014   0.1511
  -2.000   0.2248   0.02024   0.01029  -0.0982   0.7956   0.1579
  -1.750   0.2495   0.02011   0.01007  -0.0974   0.7883   0.1659
  -1.500   0.2826   0.01979   0.00980  -0.0983   0.7838   0.1741
  -1.250   0.3066   0.01968   0.00963  -0.0974   0.7764   0.1819
  -1.000   0.3340   0.01944   0.00944  -0.0971   0.7699   0.1887
  -0.750   0.3691   0.01910   0.00904  -0.0982   0.7655   0.1980
  -0.500   0.3878   0.01904   0.00908  -0.0964   0.7566   0.2058
  -0.250   0.4188   0.01878   0.00881  -0.0967   0.7509   0.2165
   0.000   0.4446   0.01863   0.00870  -0.0962   0.7439   0.2278
   0.250   0.4706   0.01848   0.00861  -0.0956   0.7364   0.2411
   0.500   0.5061   0.01817   0.00834  -0.0968   0.7314   0.2627
   0.750   0.5255   0.01818   0.00848  -0.0952   0.7218   0.2865
   1.250   0.5769   0.01756   0.00839  -0.0941   0.7054   0.4319
   1.750   0.7095   0.01617   0.00798  -0.1085   0.6789   1.0000
   2.000   0.7307   0.01623   0.00794  -0.1069   0.6668   1.0000
   2.250   0.7501   0.01638   0.00803  -0.1051   0.6559   1.0000
   2.500   0.7743   0.01645   0.00800  -0.1041   0.6466   1.0000
   2.750   0.7940   0.01660   0.00810  -0.1023   0.6354   1.0000
   3.000   0.8142   0.01675   0.00820  -0.1006   0.6245   1.0000
   3.250   0.8372   0.01685   0.00822  -0.0994   0.6140   1.0000
   3.500   0.8567   0.01701   0.00834  -0.0977   0.6020   1.0000
   3.750   0.8759   0.01718   0.00849  -0.0958   0.5896   1.0000
   4.000   0.8962   0.01735   0.00859  -0.0942   0.5773   1.0000
   4.250   0.9168   0.01751   0.00869  -0.0926   0.5645   1.0000
   4.500   0.9363   0.01770   0.00884  -0.0908   0.5512   1.0000
   4.750   0.9541   0.01793   0.00904  -0.0888   0.5370   1.0000
   5.000   0.9718   0.01817   0.00923  -0.0867   0.5221   1.0000
   5.250   0.9891   0.01843   0.00945  -0.0846   0.5064   1.0000
   5.500   1.0056   0.01872   0.00968  -0.0824   0.4900   1.0000
   5.750   1.0215   0.01904   0.00993  -0.0800   0.4732   1.0000
   6.000   1.0366   0.01939   0.01022  -0.0776   0.4560   1.0000
   6.250   1.0501   0.01977   0.01054  -0.0750   0.4384   1.0000
   6.500   1.0622   0.02019   0.01087  -0.0721   0.4206   1.0000
   6.750   1.0737   0.02065   0.01125  -0.0691   0.4029   1.0000
   7.000   1.0852   0.02116   0.01169  -0.0663   0.3860   1.0000
   7.250   1.0970   0.02171   0.01217  -0.0637   0.3699   1.0000
   7.500   1.1090   0.02230   0.01270  -0.0611   0.3549   1.0000
   7.750   1.1211   0.02293   0.01327  -0.0587   0.3408   1.0000
   8.000   1.1340   0.02357   0.01387  -0.0564   0.3283   1.0000
   8.250   1.1472   0.02424   0.01451  -0.0543   0.3174   1.0000
   8.500   1.1603   0.02494   0.01515  -0.0522   0.3073   1.0000
   8.750   1.1740   0.02563   0.01586  -0.0503   0.2975   1.0000
   9.000   1.1874   0.02638   0.01654  -0.0484   0.2892   1.0000
   9.250   1.2013   0.02710   0.01734  -0.0467   0.2807   1.0000
   9.500   1.2149   0.02789   0.01806  -0.0449   0.2735   1.0000
   9.750   1.2289   0.02865   0.01891  -0.0433   0.2660   1.0000
  10.000   1.2429   0.02945   0.01970  -0.0417   0.2597   1.0000
  10.250   1.2572   0.03026   0.02057  -0.0401   0.2534   1.0000
  10.500   1.2698   0.03112   0.02151  -0.0385   0.2468   1.0000
  10.750   1.2829   0.03201   0.02236  -0.0369   0.2408   1.0000
  11.000   1.2931   0.03298   0.02347  -0.0352   0.2338   1.0000
  11.250   1.3037   0.03397   0.02447  -0.0335   0.2276   1.0000
  11.500   1.3134   0.03503   0.02563  -0.0319   0.2212   1.0000
  11.750   1.3233   0.03611   0.02682  -0.0303   0.2154   1.0000
  12.000   1.3333   0.03720   0.02790  -0.0288   0.2101   1.0000
  12.250   1.3402   0.03848   0.02935  -0.0272   0.2039   1.0000
  12.500   1.3463   0.03981   0.03078  -0.0256   0.1979   1.0000
  12.750   1.3531   0.04115   0.03217  -0.0242   0.1926   1.0000
  13.000   1.3581   0.04268   0.03390  -0.0228   0.1865   1.0000
  13.250   1.3624   0.04425   0.03555  -0.0214   0.1812   1.0000
  13.500   1.3663   0.04595   0.03737  -0.0202   0.1756   1.0000
  13.750   1.3691   0.04780   0.03940  -0.0191   0.1696   1.0000
  14.000   1.3690   0.04987   0.04150  -0.0180   0.1638   1.0000
  14.250   1.3704   0.05204   0.04390  -0.0172   0.1570   1.0000
  14.500   1.3698   0.05441   0.04637  -0.0165   0.1514   1.0000
  14.750   1.3700   0.05687   0.04901  -0.0159   0.1453   1.0000
  15.000   1.3669   0.05974   0.05198  -0.0155   0.1387   1.0000
  15.250   1.3631   0.06286   0.05525  -0.0154   0.1314   1.0000
  15.500   1.3546   0.06663   0.05907  -0.0156   0.1235   1.0000
  15.750   1.3480   0.07039   0.06298  -0.0159   0.1153   1.0000
  16.000   1.3368   0.07489   0.06756  -0.0166   0.1066   1.0000
  16.250   1.3231   0.07993   0.07266  -0.0177   0.0992   1.0000
  16.500   1.3089   0.08529   0.07813  -0.0190   0.0906   1.0000
  16.750   1.2927   0.09114   0.08408  -0.0208   0.0838   1.0000
  17.000   1.2737   0.09766   0.09069  -0.0230   0.0775   1.0000
  17.250   1.2556   0.10427   0.09742  -0.0255   0.0703   1.0000
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