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GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 507 AIRFOIL (goe507-il)
Reynolds number: 200,000
Max Cl/Cd: 73.76 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe507-il-200000.txt
Download as CSV file: xf-goe507-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 507 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4209   0.08781   0.08411  -0.0326   1.0000   0.0650
  -8.500  -0.4246   0.08463   0.08098  -0.0340   1.0000   0.0676
  -8.250  -0.4412   0.08121   0.07765  -0.0365   1.0000   0.0695
  -8.000  -0.3693   0.06682   0.06353  -0.0366   1.0000   0.0744
  -7.750  -0.3768   0.06462   0.06138  -0.0347   1.0000   0.0756
  -7.500  -0.5014   0.06743   0.06392  -0.0424   1.0000   0.0720
  -7.250  -0.4942   0.06697   0.06358  -0.0371   1.0000   0.0734
  -7.000  -0.4936   0.06597   0.06261  -0.0334   1.0000   0.0748
  -6.750  -0.4966   0.06399   0.06063  -0.0314   1.0000   0.0764
  -6.500  -0.4990   0.06137   0.05797  -0.0305   1.0000   0.0792
  -6.250  -0.5013   0.05334   0.04955  -0.0363   0.9986   0.0864
  -6.000  -0.4749   0.05206   0.04834  -0.0367   0.9956   0.0890
  -5.750  -0.4575   0.03412   0.02869  -0.0448   0.9885   0.0721
  -5.500  -0.4307   0.02985   0.02394  -0.0464   0.9851   0.0726
  -5.250  -0.3998   0.02853   0.02273  -0.0481   0.9820   0.0760
  -5.000  -0.3735   0.02559   0.01928  -0.0486   0.9773   0.0765
  -4.750  -0.3417   0.02401   0.01740  -0.0498   0.9737   0.0794
  -4.500  -0.3061   0.02226   0.01524  -0.0515   0.9709   0.0811
  -4.250  -0.2755   0.02127   0.01392  -0.0521   0.9649   0.0835
  -4.000  -0.2375   0.02034   0.01270  -0.0540   0.9600   0.0847
  -3.750  -0.1972   0.01849   0.01070  -0.0566   0.9569   0.0872
  -3.500  -0.1664   0.01775   0.00992  -0.0573   0.9512   0.0897
  -3.250  -0.1326   0.01707   0.00918  -0.0584   0.9467   0.0915
  -3.000  -0.0943   0.01643   0.00848  -0.0604   0.9435   0.0937
  -2.750  -0.0534   0.01589   0.00789  -0.0629   0.9413   0.0969
  -2.500  -0.0272   0.01551   0.00749  -0.0625   0.9345   0.0990
  -2.250   0.0086   0.01486   0.00692  -0.0641   0.9304   0.1025
  -2.000   0.0485   0.01440   0.00650  -0.0664   0.9276   0.1072
  -1.500   0.1110   0.01375   0.00597  -0.0674   0.9162   0.1234
  -1.250   0.1473   0.01327   0.00573  -0.0689   0.9122   0.1585
  -1.000   0.1759   0.01288   0.00564  -0.0689   0.9059   0.2380
  -0.750   0.2042   0.01249   0.00549  -0.0689   0.8991   0.2994
  -0.500   0.2331   0.01159   0.00533  -0.0690   0.8946   0.4891
  -0.250   0.3549   0.01014   0.00519  -0.0873   0.8994   1.0000
   0.000   0.3820   0.01008   0.00503  -0.0867   0.8912   1.0000
   0.250   0.4065   0.01002   0.00490  -0.0856   0.8814   1.0000
   0.500   0.4290   0.00999   0.00483  -0.0841   0.8703   1.0000
   0.750   0.4529   0.00989   0.00466  -0.0827   0.8589   1.0000
   1.000   0.4772   0.00977   0.00446  -0.0812   0.8469   1.0000
   1.250   0.4996   0.00971   0.00436  -0.0795   0.8337   1.0000
   1.500   0.5221   0.00969   0.00431  -0.0780   0.8206   1.0000
   1.750   0.5451   0.00964   0.00422  -0.0765   0.8062   1.0000
   2.000   0.5682   0.00958   0.00411  -0.0749   0.7901   1.0000
   2.250   0.5915   0.00952   0.00398  -0.0734   0.7721   1.0000
   2.500   0.6142   0.00950   0.00392  -0.0718   0.7521   1.0000
   2.750   0.6372   0.00953   0.00391  -0.0704   0.7317   1.0000
   3.000   0.6607   0.00957   0.00389  -0.0691   0.7104   1.0000
   3.250   0.6831   0.00963   0.00390  -0.0675   0.6832   1.0000
   3.500   0.7051   0.00974   0.00390  -0.0659   0.6515   1.0000
   3.750   0.7270   0.00992   0.00396  -0.0644   0.6190   1.0000
   4.000   0.7487   0.01015   0.00407  -0.0628   0.5862   1.0000
   4.250   0.7695   0.01046   0.00423  -0.0612   0.5517   1.0000
   4.500   0.7899   0.01084   0.00444  -0.0595   0.5169   1.0000
   4.750   0.8098   0.01124   0.00470  -0.0578   0.4815   1.0000
   5.000   0.8295   0.01164   0.00497  -0.0562   0.4411   1.0000
   5.250   0.8480   0.01211   0.00526  -0.0543   0.3928   1.0000
   5.500   0.8643   0.01275   0.00560  -0.0522   0.3297   1.0000
   5.750   0.8768   0.01376   0.00613  -0.0496   0.2396   1.0000
   6.000   0.8864   0.01523   0.00690  -0.0468   0.1311   1.0000
   6.250   0.9025   0.01620   0.00765  -0.0449   0.1059   1.0000
   6.500   0.9194   0.01707   0.00845  -0.0430   0.0953   1.0000
   6.750   0.9369   0.01786   0.00926  -0.0413   0.0876   1.0000
   7.000   0.9526   0.01885   0.01025  -0.0393   0.0814   1.0000
   7.250   0.9700   0.01971   0.01113  -0.0376   0.0757   1.0000
   7.500   0.9846   0.02119   0.01252  -0.0356   0.0704   1.0000
   7.750   1.0043   0.02197   0.01340  -0.0342   0.0658   1.0000
   8.000   1.0232   0.02311   0.01452  -0.0329   0.0615   1.0000
   8.250   1.0449   0.02495   0.01636  -0.0321   0.0575   1.0000
   8.500   1.0652   0.02581   0.01735  -0.0309   0.0538   1.0000
   8.750   1.0862   0.02699   0.01858  -0.0299   0.0509   1.0000
   9.000   1.1130   0.02992   0.02147  -0.0304   0.0476   1.0000
   9.250   1.1298   0.03057   0.02238  -0.0285   0.0456   1.0000
   9.500   1.1483   0.03179   0.02378  -0.0271   0.0432   1.0000
   9.750   1.1676   0.03332   0.02543  -0.0260   0.0415   1.0000
  10.000   1.1861   0.03504   0.02724  -0.0251   0.0400   1.0000
  10.250   1.2039   0.03874   0.03110  -0.0245   0.0384   1.0000
  10.500   1.2116   0.04001   0.03275  -0.0216   0.0373   1.0000
  10.750   1.2185   0.04204   0.03511  -0.0190   0.0362   1.0000
  11.000   1.2227   0.04474   0.03814  -0.0163   0.0354   1.0000
  11.250   1.2227   0.04757   0.04129  -0.0134   0.0350   1.0000
  11.500   1.2162   0.05049   0.04451  -0.0099   0.0348   1.0000
  11.750   1.2040   0.05348   0.04778  -0.0060   0.0348   1.0000
  12.000   1.1881   0.05668   0.05125  -0.0027   0.0347   1.0000
  12.250   1.1693   0.06030   0.05512  -0.0001   0.0348   1.0000
  12.500   1.1475   0.06443   0.05950   0.0016   0.0350   1.0000
  12.750   1.1242   0.06907   0.06437   0.0021   0.0353   1.0000
  13.000   1.0980   0.07455   0.07006   0.0013   0.0357   1.0000
  13.250   1.0725   0.08058   0.07627  -0.0007   0.0362   1.0000
  13.500   1.0450   0.08769   0.08355  -0.0042   0.0366   1.0000
  13.750   1.0178   0.09570   0.09170  -0.0090   0.0370   1.0000
  14.000   0.9936   0.10443   0.10051  -0.0141   0.0377   1.0000
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