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GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 11K AIRFOIL (goe11k-il)
Reynolds number: 50,000
Max Cl/Cd: 28.16 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe11k-il-50000.txt
Download as CSV file: xf-goe11k-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 11K AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4948   0.10681   0.09990  -0.0206   1.0000   0.2168
  -8.000  -0.4829   0.10251   0.09561  -0.0186   1.0000   0.2279
  -7.750  -0.5135   0.10232   0.09561  -0.0173   1.0000   0.2320
  -7.500  -0.5014   0.09811   0.09141  -0.0151   1.0000   0.2447
  -7.250  -0.5029   0.09507   0.08843  -0.0130   1.0000   0.2536
  -7.000  -0.5313   0.09428   0.08781  -0.0118   1.0000   0.2616
  -6.750  -0.5270   0.09089   0.08446  -0.0092   1.0000   0.2752
  -6.500  -0.5288   0.08797   0.08159  -0.0069   1.0000   0.2895
  -6.250  -0.5368   0.08551   0.07918  -0.0051   1.0000   0.3055
  -6.000  -0.5287   0.08216   0.07587  -0.0009   1.0000   0.3291
  -5.750  -0.5452   0.08046   0.07425   0.0007   1.0000   0.3510
  -5.500  -0.5356   0.07713   0.07097   0.0063   1.0000   0.3842
  -5.250  -0.5296   0.07443   0.06831   0.0115   1.0000   0.4199
  -4.750  -0.2194   0.05653   0.04935   0.0017   1.0000   0.9024
  -4.500  -0.2388   0.05550   0.04845   0.0067   1.0000   0.8819
  -4.250  -0.2915   0.05605   0.04927   0.0172   1.0000   0.8406
  -3.750  -0.4374   0.04450   0.03619  -0.0222   1.0000   0.2058
  -3.500  -0.4106   0.04041   0.03141  -0.0226   1.0000   0.1809
  -3.250  -0.3855   0.03757   0.02765  -0.0221   1.0000   0.1730
  -3.000  -0.3650   0.03514   0.02505  -0.0211   1.0000   0.1776
  -2.750  -0.3412   0.03298   0.02232  -0.0201   1.0000   0.1769
  -2.500  -0.3188   0.03140   0.02039  -0.0189   1.0000   0.1839
  -2.250  -0.2949   0.02991   0.01845  -0.0178   1.0000   0.1896
  -2.000  -0.2709   0.02852   0.01690  -0.0169   1.0000   0.1951
  -1.750  -0.2464   0.02748   0.01562  -0.0162   1.0000   0.2067
  -1.500  -0.2205   0.02654   0.01445  -0.0155   1.0000   0.2155
  -1.250  -0.1910   0.02566   0.01346  -0.0155   1.0000   0.2265
  -1.000  -0.1618   0.02501   0.01271  -0.0155   1.0000   0.2475
  -0.750  -0.1339   0.02427   0.01211  -0.0155   1.0000   0.2774
  -0.500  -0.0598   0.02111   0.01112  -0.0233   1.0000   1.0000
  -0.250  -0.0389   0.02133   0.01092  -0.0221   1.0000   1.0000
   0.000  -0.0182   0.02157   0.01087  -0.0209   1.0000   1.0000
   0.250   0.0023   0.02182   0.01088  -0.0199   1.0000   1.0000
   0.500   0.0227   0.02210   0.01096  -0.0189   1.0000   1.0000
   0.750   0.0432   0.02240   0.01110  -0.0179   1.0000   1.0000
   1.000   0.0636   0.02271   0.01129  -0.0169   1.0000   1.0000
   1.250   0.0839   0.02305   0.01152  -0.0160   1.0000   1.0000
   1.500   0.1041   0.02341   0.01180  -0.0151   1.0000   1.0000
   1.750   0.1243   0.02379   0.01212  -0.0142   1.0000   1.0000
   2.000   0.1443   0.02419   0.01249  -0.0134   1.0000   1.0000
   2.250   0.1643   0.02462   0.01291  -0.0126   1.0000   1.0000
   2.500   0.1840   0.02508   0.01337  -0.0118   1.0000   1.0000
   2.750   0.2036   0.02557   0.01388  -0.0110   1.0000   1.0000
   3.000   0.2230   0.02609   0.01444  -0.0102   1.0000   1.0000
   3.250   0.2421   0.02665   0.01506  -0.0095   1.0000   1.0000
   3.500   0.2609   0.02726   0.01576  -0.0088   1.0000   1.0000
   3.750   0.2792   0.02791   0.01651  -0.0081   1.0000   1.0000
   4.000   0.2971   0.02863   0.01734  -0.0075   1.0000   1.0000
   4.250   0.3142   0.02942   0.01827  -0.0069   1.0000   1.0000
   4.500   0.3306   0.03032   0.01934  -0.0064   1.0000   1.0000
   4.750   0.3458   0.03133   0.02053  -0.0059   1.0000   1.0000
   5.000   0.3595   0.03253   0.02192  -0.0056   1.0000   1.0000
   5.250   0.6442   0.02784   0.01919  -0.0414   0.8170   1.0000
   5.500   0.7409   0.02631   0.01437  -0.0401   0.2391   1.0000
   5.750   0.8119   0.02910   0.01692  -0.0475   0.1908   1.0000
   6.000   0.8647   0.03199   0.01985  -0.0515   0.1660   1.0000
   6.250   0.8982   0.03461   0.02267  -0.0520   0.1506   1.0000
   6.500   0.9288   0.03769   0.02595  -0.0521   0.1410   1.0000
   6.750   0.9489   0.04016   0.02885  -0.0501   0.1330   1.0000
   7.000   0.9735   0.04381   0.03274  -0.0493   0.1297   1.0000
   7.250   0.9863   0.04710   0.03654  -0.0463   0.1278   1.0000
   7.500   0.9927   0.05008   0.04012  -0.0423   0.1262   1.0000
   7.750   0.9988   0.05356   0.04407  -0.0387   0.1260   1.0000
   8.000   1.0092   0.05800   0.04877  -0.0363   0.1282   1.0000
   8.250   0.9950   0.06165   0.05328  -0.0303   0.1361   1.0000
   8.500   1.0046   0.06707   0.05883  -0.0285   0.1423   1.0000
   8.750   0.9850   0.07174   0.06407  -0.0239   0.1554   1.0000
   9.000   0.9527   0.07708   0.06987  -0.0201   0.1754   1.0000
   9.250   0.9198   0.08334   0.07632  -0.0183   0.1977   1.0000
   9.500   0.8632   0.08968   0.08267  -0.0189   0.2198   1.0000
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