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GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 420 AIRFOIL (goe420-il)
Reynolds number: 50,000
Max Cl/Cd: 4.01 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe420-il-50000.txt
Download as CSV file: xf-goe420-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 420 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3683   0.12595   0.11999  -0.0067   1.0000   0.3132
  -7.250  -0.6101   0.09286   0.08692  -0.0292   1.0000   0.1689
  -7.000  -0.6152   0.08953   0.08359  -0.0281   1.0000   0.1677
  -6.750  -0.6299   0.08461   0.07864  -0.0282   1.0000   0.1660
  -6.500  -0.6544   0.07723   0.07111  -0.0300   1.0000   0.1634
  -6.250  -0.6812   0.06743   0.06085  -0.0335   1.0000   0.1605
  -6.000  -0.6859   0.06140   0.05437  -0.0349   1.0000   0.1608
  -5.750  -0.6818   0.05697   0.04950  -0.0356   1.0000   0.1626
  -5.500  -0.6733   0.05307   0.04506  -0.0360   1.0000   0.1653
  -5.250  -0.6614   0.04963   0.04096  -0.0364   1.0000   0.1681
  -5.000  -0.6468   0.04802   0.03934  -0.0357   1.0000   0.1722
  -4.750  -0.6316   0.04696   0.03822  -0.0349   1.0000   0.1785
  -4.500  -0.6156   0.04514   0.03600  -0.0346   1.0000   0.1859
  -4.250  -0.5998   0.04452   0.03550  -0.0337   1.0000   0.1941
  -4.000  -0.5835   0.04357   0.03445  -0.0331   1.0000   0.2050
  -3.750  -0.5671   0.04294   0.03376  -0.0324   1.0000   0.2193
  -3.500  -0.5514   0.04274   0.03365  -0.0315   1.0000   0.2369
  -3.250  -0.4438   0.04714   0.03843  -0.0444   0.9475   0.3123
  -3.000  -0.4081   0.04851   0.03996  -0.0456   0.9307   0.3522
  -2.750  -0.3906   0.04913   0.04067  -0.0443   0.9212   0.3796
  -2.500  -0.3619   0.04995   0.04148  -0.0446   0.9067   0.4108
  -2.250  -0.3300   0.05107   0.04269  -0.0449   0.8923   0.4411
  -2.000  -0.3148   0.05144   0.04306  -0.0435   0.8838   0.4662
  -1.750  -0.2877   0.05209   0.04370  -0.0434   0.8720   0.4939
  -1.500  -0.2726   0.05229   0.04386  -0.0423   0.8648   0.5142
  -1.250  -0.2437   0.05279   0.04431  -0.0426   0.8524   0.5368
  -1.000  -0.2845   0.05321   0.04485  -0.0361   0.8997   0.5378
  -0.750  -0.1946   0.05386   0.04527  -0.0428   0.8354   0.5777
  -0.500  -0.1885   0.05423   0.04562  -0.0409   0.8323   0.5923
  -0.250  -0.1789   0.05475   0.04615  -0.0393   0.8297   0.6074
   0.000  -0.1740   0.05570   0.04708  -0.0381   0.8406   0.6221
   0.250  -0.1457   0.05710   0.04844  -0.0390   0.8371   0.6434
   0.500  -0.2129   0.05703   0.04847  -0.0300   0.9130   0.6399
   0.750  -0.1958   0.05719   0.04860  -0.0296   0.9018   0.6594
   1.000  -0.1624   0.05954   0.05093  -0.0314   0.8954   0.6864
   1.250  -0.1585   0.05895   0.05038  -0.0290   0.8895   0.7067
   1.500  -0.1336   0.06001   0.05146  -0.0296   0.8802   0.7380
   1.750  -0.1084   0.06178   0.05336  -0.0300   0.8755   0.7722
   2.000  -0.1016   0.06126   0.05301  -0.0279   0.8660   0.8042
   2.250  -0.0615   0.06317   0.05524  -0.0311   0.8587   0.8788
   2.500  -0.0176   0.06419   0.05625  -0.0394   0.8502   1.0000
   2.750   0.0244   0.06643   0.05804  -0.0458   0.8400   1.0000
   3.000   0.0515   0.06881   0.06010  -0.0486   0.8355   1.0000
   3.250   0.0628   0.06918   0.06028  -0.0484   0.8243   1.0000
   3.500   0.1060   0.07308   0.06390  -0.0525   0.8175   1.0000
   3.750   0.1016   0.07256   0.06329  -0.0500   0.8084   1.0000
   4.000   0.1344   0.07526   0.06580  -0.0524   0.7999   1.0000
   4.250   0.1427   0.07645   0.06688  -0.0516   0.7930   1.0000
   4.500   0.1661   0.07828   0.06859  -0.0526   0.7822   1.0000
   4.750   0.1888   0.08099   0.07118  -0.0538   0.7767   1.0000
   5.000   0.1990   0.08171   0.07183  -0.0531   0.7642   1.0000
   5.250   0.2308   0.08530   0.07531  -0.0554   0.7584   1.0000
   5.500   0.2319   0.08540   0.07537  -0.0536   0.7461   1.0000
   5.750   0.2704   0.08960   0.07946  -0.0566   0.7399   1.0000
   6.000   0.2642   0.08927   0.07912  -0.0542   0.7278   1.0000
   6.250   0.3055   0.09373   0.08349  -0.0573   0.7214   1.0000
   6.500   0.2952   0.09329   0.08305  -0.0546   0.7098   1.0000
   6.750   0.3362   0.09771   0.08739  -0.0576   0.7028   1.0000
   7.000   0.3243   0.09745   0.08714  -0.0550   0.6924   1.0000
   7.250   0.3586   0.10112   0.09076  -0.0572   0.6850   1.0000
   7.500   0.3530   0.10179   0.09142  -0.0555   0.6753   1.0000
   7.750   0.3832   0.10502   0.09462  -0.0572   0.6670   1.0000
   8.000   0.3831   0.10656   0.09615  -0.0563   0.6602   1.0000
   8.250   0.4013   0.10879   0.09837  -0.0568   0.6504   1.0000
   8.500   0.4274   0.11275   0.10231  -0.0583   0.6456   1.0000
   8.750   0.4229   0.11305   0.10263  -0.0569   0.6340   1.0000
   9.000   0.4566   0.11730   0.10687  -0.0589   0.6284   1.0000
   9.250   0.4458   0.11781   0.10739  -0.0574   0.6204   1.0000
   9.500   0.4683   0.12063   0.11022  -0.0583   0.6119   1.0000
   9.750   0.4841   0.12396   0.11356  -0.0591   0.6071   1.0000
  10.000   0.4849   0.12485   0.11447  -0.0584   0.5964   1.0000
  10.250   0.5188   0.12947   0.11912  -0.0603   0.5907   1.0000
  10.500   0.5065   0.12966   0.11932  -0.0590   0.5815   1.0000
  10.750   0.5322   0.13307   0.12276  -0.0601   0.5735   1.0000
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