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GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 564 AIRFOIL (goe564-il)
Reynolds number: 50,000
Max Cl/Cd: 37.5 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe564-il-50000-n5.txt
Download as CSV file: xf-goe564-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4574   0.09485   0.08771  -0.0353   1.0000   0.0639
  -8.500  -0.4587   0.09147   0.08439  -0.0351   1.0000   0.0634
  -8.250  -0.4650   0.08809   0.08111  -0.0354   1.0000   0.0632
  -8.000  -0.4705   0.08423   0.07733  -0.0366   1.0000   0.0632
  -7.750  -0.4769   0.07995   0.07310  -0.0385   1.0000   0.0634
  -7.500  -0.4822   0.07548   0.06863  -0.0402   1.0000   0.0637
  -7.250  -0.4864   0.07080   0.06391  -0.0416   1.0000   0.0639
  -7.000  -0.4891   0.06604   0.05903  -0.0426   1.0000   0.0642
  -6.750  -0.4864   0.06237   0.05531  -0.0422   1.0000   0.0650
  -6.500  -0.4829   0.05825   0.05104  -0.0421   1.0000   0.0652
  -6.250  -0.4764   0.05472   0.04736  -0.0416   1.0000   0.0659
  -6.000  -0.4667   0.05230   0.04482  -0.0406   1.0000   0.0680
  -5.750  -0.4562   0.04934   0.04163  -0.0401   1.0000   0.0713
  -5.500  -0.4447   0.04543   0.03727  -0.0400   1.0000   0.0735
  -5.250  -0.4305   0.04159   0.03291  -0.0396   1.0000   0.0746
  -5.000  -0.4139   0.03807   0.02879  -0.0391   1.0000   0.0760
  -4.750  -0.3963   0.03596   0.02639  -0.0382   1.0000   0.0794
  -4.500  -0.3778   0.03465   0.02493  -0.0372   1.0000   0.0838
  -4.250  -0.3571   0.03248   0.02228  -0.0365   1.0000   0.0869
  -4.000  -0.3348   0.03037   0.01961  -0.0356   1.0000   0.0897
  -3.750  -0.3128   0.02879   0.01774  -0.0348   1.0000   0.0927
  -3.500  -0.2910   0.02766   0.01646  -0.0339   1.0000   0.0968
  -3.250  -0.2680   0.02666   0.01508  -0.0330   1.0000   0.1047
  -3.000  -0.2465   0.02592   0.01435  -0.0322   1.0000   0.1133
  -2.750  -0.2227   0.02500   0.01321  -0.0314   1.0000   0.1229
  -2.500  -0.1994   0.02426   0.01229  -0.0305   1.0000   0.1348
  -2.250  -0.1768   0.02373   0.01172  -0.0298   1.0000   0.1517
  -2.000  -0.1546   0.02330   0.01132  -0.0292   1.0000   0.1727
  -1.750  -0.1323   0.02292   0.01092  -0.0285   1.0000   0.1976
  -1.500  -0.1101   0.02253   0.01057  -0.0279   1.0000   0.2199
  -1.250  -0.0791   0.02219   0.01032  -0.0291   0.9960   0.2496
  -1.000  -0.0434   0.02177   0.01012  -0.0312   0.9895   0.2965
  -0.750   0.0020   0.01941   0.01016  -0.0341   0.9867   1.0000
  -0.500   0.0394   0.01978   0.01007  -0.0363   0.9785   1.0000
  -0.250   0.0756   0.02013   0.01012  -0.0384   0.9700   1.0000
   0.000   0.1128   0.02050   0.01025  -0.0407   0.9616   1.0000
   0.250   0.1491   0.02084   0.01039  -0.0428   0.9524   1.0000
   0.500   0.1827   0.02113   0.01053  -0.0443   0.9420   1.0000
   0.750   0.2185   0.02143   0.01072  -0.0462   0.9323   1.0000
   1.000   0.2563   0.02172   0.01091  -0.0484   0.9226   1.0000
   1.250   0.2886   0.02195   0.01109  -0.0495   0.9108   1.0000
   1.500   0.3224   0.02218   0.01129  -0.0509   0.8993   1.0000
   1.750   0.3584   0.02237   0.01147  -0.0525   0.8883   1.0000
   2.000   0.3978   0.02246   0.01159  -0.0546   0.8769   1.0000
   2.250   0.4342   0.02235   0.01152  -0.0557   0.8597   1.0000
   2.500   0.4771   0.02190   0.01112  -0.0573   0.8392   1.0000
   2.750   0.5193   0.02137   0.01067  -0.0586   0.8186   1.0000
   3.000   0.5489   0.02120   0.01057  -0.0580   0.7975   1.0000
   3.250   0.5804   0.02105   0.01053  -0.0579   0.7788   1.0000
   3.500   0.6098   0.02094   0.01051  -0.0574   0.7580   1.0000
   3.750   0.6367   0.02086   0.01054  -0.0564   0.7343   1.0000
   4.000   0.6641   0.02077   0.01058  -0.0554   0.7077   1.0000
   4.250   0.6943   0.02063   0.01051  -0.0548   0.6780   1.0000
   4.500   0.7270   0.02048   0.01037  -0.0544   0.6439   1.0000
   4.750   0.7552   0.02056   0.01045  -0.0534   0.6026   1.0000
   5.000   0.7790   0.02085   0.01064  -0.0518   0.5522   1.0000
   5.250   0.7988   0.02130   0.01094  -0.0497   0.4931   1.0000
   5.500   0.8172   0.02195   0.01128  -0.0475   0.4351   1.0000
   5.750   0.8346   0.02278   0.01186  -0.0454   0.3863   1.0000
   6.000   0.8528   0.02368   0.01256  -0.0438   0.3491   1.0000
   6.250   0.8728   0.02456   0.01338  -0.0425   0.3220   1.0000
   6.500   0.8937   0.02548   0.01426  -0.0413   0.2998   1.0000
   6.750   0.9149   0.02641   0.01526  -0.0403   0.2786   1.0000
   7.000   0.9366   0.02740   0.01627  -0.0393   0.2595   1.0000
   7.250   0.9597   0.02845   0.01742  -0.0386   0.2416   1.0000
   7.500   0.9780   0.02949   0.01855  -0.0372   0.2196   1.0000
   7.750   0.9907   0.03043   0.01951  -0.0351   0.1947   1.0000
   8.000   1.0028   0.03137   0.02054  -0.0330   0.1716   1.0000
   8.250   1.0175   0.03247   0.02182  -0.0312   0.1499   1.0000
   8.500   1.0276   0.03357   0.02292  -0.0289   0.1276   1.0000
   8.750   1.0386   0.03495   0.02435  -0.0267   0.1060   1.0000
   9.000   1.0475   0.03662   0.02589  -0.0245   0.0908   1.0000
   9.250   1.0594   0.03866   0.02797  -0.0226   0.0788   1.0000
   9.500   1.0724   0.04080   0.03031  -0.0209   0.0693   1.0000
   9.750   1.0813   0.04282   0.03233  -0.0189   0.0630   1.0000
  10.000   1.0951   0.04522   0.03513  -0.0172   0.0577   1.0000
  10.250   1.1020   0.04723   0.03731  -0.0151   0.0539   1.0000
  10.500   1.1081   0.04970   0.04000  -0.0132   0.0506   1.0000
  10.750   1.1120   0.05251   0.04316  -0.0111   0.0480   1.0000
  11.000   1.1134   0.05550   0.04644  -0.0091   0.0464   1.0000
  11.250   1.1117   0.05846   0.04963  -0.0073   0.0451   1.0000
  11.500   1.1083   0.06131   0.05261  -0.0058   0.0437   1.0000
  11.750   1.1050   0.06448   0.05588  -0.0046   0.0426   1.0000
  12.000   1.0908   0.06869   0.06039  -0.0039   0.0422   1.0000
  12.250   1.0733   0.07352   0.06553  -0.0041   0.0419   1.0000
  12.500   1.0541   0.07895   0.07122  -0.0053   0.0418   1.0000
  12.750   1.0334   0.08518   0.07766  -0.0078   0.0419   1.0000
  13.000   1.0130   0.09202   0.08467  -0.0113   0.0422   1.0000
  13.250   0.9912   0.09994   0.09272  -0.0159   0.0425   1.0000
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