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GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 5K AIRFOIL (goe05k-il)
Reynolds number: 50,000
Max Cl/Cd: 21.21 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe05k-il-50000-n5.txt
Download as CSV file: xf-goe05k-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 5K 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5394   0.10499   0.09811  -0.0103   1.0000   0.0790
  -8.000  -0.5445   0.10310   0.09634  -0.0128   1.0000   0.0811
  -7.750  -0.5471   0.10110   0.09444  -0.0176   1.0000   0.0820
  -7.500  -0.5375   0.09536   0.08870  -0.0138   1.0000   0.0863
  -7.250  -0.5333   0.09201   0.08539  -0.0150   1.0000   0.0916
  -7.000  -0.5314   0.08970   0.08312  -0.0211   1.0000   0.0956
  -6.750  -0.5253   0.08496   0.07845  -0.0198   1.0000   0.0997
  -6.500  -0.5183   0.08157   0.07506  -0.0209   1.0000   0.1076
  -6.000  -0.5023   0.07509   0.06848  -0.0282   1.0000   0.1256
  -5.750  -0.4930   0.07159   0.06494  -0.0290   1.0000   0.1400
  -5.500  -0.4845   0.06736   0.06076  -0.0278   1.0000   0.1556
  -5.250  -0.4754   0.06341   0.05684  -0.0262   1.0000   0.1726
  -4.250  -0.3695   0.04606   0.03815  -0.0353   1.0000   0.0626
  -4.000  -0.3394   0.04283   0.03424  -0.0353   1.0000   0.0441
  -3.750  -0.3195   0.03897   0.03018  -0.0349   1.0000   0.0392
  -3.500  -0.2951   0.03592   0.02667  -0.0343   1.0000   0.0349
  -3.250  -0.2712   0.03307   0.02340  -0.0336   1.0000   0.0331
  -3.000  -0.2463   0.03053   0.02037  -0.0327   1.0000   0.0326
  -2.750  -0.2207   0.02818   0.01749  -0.0317   1.0000   0.0331
  -2.500  -0.1948   0.02609   0.01494  -0.0307   1.0000   0.0335
  -2.250  -0.1685   0.02412   0.01254  -0.0295   1.0000   0.0336
  -2.000  -0.1415   0.02244   0.01045  -0.0284   1.0000   0.0360
  -1.750  -0.1154   0.02095   0.00872  -0.0274   1.0000   0.0409
  -1.500  -0.0895   0.01965   0.00708  -0.0265   1.0000   0.0495
  -1.250  -0.0637   0.01856   0.00572  -0.0258   1.0000   0.0679
  -1.000  -0.0213   0.01448   0.00427  -0.0282   1.0000   1.0000
  -0.750   0.0018   0.01451   0.00364  -0.0271   1.0000   1.0000
  -0.500   0.0246   0.01456   0.00328  -0.0262   1.0000   1.0000
  -0.250   0.0472   0.01463   0.00303  -0.0254   1.0000   1.0000
   0.000   0.0698   0.01472   0.00288  -0.0245   1.0000   1.0000
   0.250   0.0923   0.01482   0.00278  -0.0237   1.0000   1.0000
   0.500   0.1147   0.01494   0.00279  -0.0230   1.0000   1.0000
   0.750   0.1371   0.01508   0.00285  -0.0222   1.0000   1.0000
   1.000   0.1592   0.01523   0.00300  -0.0214   1.0000   1.0000
   1.250   0.1814   0.01540   0.00322  -0.0207   1.0000   1.0000
   1.500   0.2033   0.01559   0.00350  -0.0199   1.0000   1.0000
   1.750   0.2252   0.01580   0.00385  -0.0191   1.0000   1.0000
   2.000   0.2469   0.01604   0.00429  -0.0183   1.0000   1.0000
   2.250   0.2685   0.01630   0.00489  -0.0175   1.0000   1.0000
   2.500   0.2900   0.01658   0.00549  -0.0168   1.0000   1.0000
   2.750   0.3114   0.01691   0.00623  -0.0160   1.0000   1.0000
   3.000   0.3325   0.01727   0.00721  -0.0150   1.0000   1.0000
   3.250   0.4908   0.02314   0.01032  -0.0343   0.0350   1.0000
   3.500   0.5201   0.02517   0.01263  -0.0337   0.0308   1.0000
   3.750   0.5520   0.02740   0.01523  -0.0330   0.0284   1.0000
   4.000   0.5820   0.03002   0.01824  -0.0321   0.0282   1.0000
   4.250   0.6094   0.03279   0.02146  -0.0310   0.0285   1.0000
   4.500   0.6343   0.03573   0.02492  -0.0296   0.0288   1.0000
   4.750   0.6569   0.03880   0.02850  -0.0280   0.0290   1.0000
   5.000   0.6774   0.04211   0.03228  -0.0264   0.0293   1.0000
   5.250   0.6957   0.04570   0.03625  -0.0249   0.0300   1.0000
   5.500   0.7156   0.04896   0.04020  -0.0230   0.0331   1.0000
   5.750   0.7312   0.05296   0.04459  -0.0215   0.0361   1.0000
   6.000   0.7468   0.05710   0.04915  -0.0202   0.0420   1.0000
   6.250   0.7619   0.06156   0.05403  -0.0192   0.0523   1.0000
   8.750   0.6747   0.09917   0.09315  -0.0273   0.1357   1.0000
   9.000   0.6784   0.10367   0.09765  -0.0272   0.1298   1.0000
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