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GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 492 AIRFOIL (goe492-il)
Reynolds number: 500,000
Max Cl/Cd: 111.96 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe492-il-500000.txt
Download as CSV file: xf-goe492-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 492 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.3772   0.15657   0.15427  -0.0173   1.0000   0.0097
 -14.250  -0.3760   0.15490   0.15260  -0.0187   1.0000   0.0098
 -12.250  -0.4594   0.14014   0.13768  -0.0181   1.0000   0.0104
  -7.250  -0.3562   0.06295   0.06106  -0.0360   0.9952   0.0166
  -7.000  -0.3457   0.05684   0.05494  -0.0421   0.9913   0.0172
  -6.750  -0.3293   0.05265   0.05074  -0.0465   0.9879   0.0180
  -6.500  -0.3097   0.04725   0.04531  -0.0537   0.9850   0.0187
  -6.250  -0.2857   0.04128   0.03928  -0.0623   0.9829   0.0203
  -6.000  -0.2641   0.03498   0.03288  -0.0705   0.9779   0.0223
  -5.000  -0.1769   0.01915   0.01472  -0.0935   0.9705   0.0156
  -4.750  -0.1429   0.01591   0.01092  -0.0952   0.9693   0.0159
  -4.500  -0.1199   0.01293   0.00742  -0.0945   0.9642   0.0175
  -4.250  -0.0874   0.01218   0.00658  -0.0956   0.9619   0.0200
  -4.000  -0.0525   0.01186   0.00618  -0.0971   0.9601   0.0236
  -3.750  -0.0188   0.01075   0.00495  -0.0984   0.9584   0.0285
  -3.500   0.0164   0.01051   0.00466  -0.1000   0.9568   0.0352
  -3.250   0.0454   0.00998   0.00408  -0.1004   0.9530   0.0425
  -3.000   0.0749   0.00969   0.00374  -0.1007   0.9487   0.0475
  -2.750   0.1069   0.00931   0.00330  -0.1016   0.9455   0.0514
  -2.500   0.1392   0.00882   0.00279  -0.1026   0.9427   0.0578
  -2.250   0.1652   0.00860   0.00251  -0.1021   0.9364   0.0628
  -2.000   0.1950   0.00825   0.00216  -0.1024   0.9317   0.0714
  -1.750   0.2231   0.00787   0.00191  -0.1025   0.9262   0.1092
  -1.500   0.2494   0.00742   0.00189  -0.1023   0.9192   0.2603
  -1.250   0.2777   0.00733   0.00181  -0.1022   0.9130   0.2841
  -1.000   0.3046   0.00724   0.00172  -0.1019   0.9047   0.3044
  -0.750   0.3313   0.00714   0.00163  -0.1015   0.8960   0.3217
  -0.250   0.3845   0.00686   0.00148  -0.1008   0.8784   0.3627
   0.000   0.4086   0.00627   0.00151  -0.1003   0.8697   0.5664
   0.250   0.4477   0.00524   0.00151  -0.1025   0.8625   1.0000
   0.500   0.4736   0.00526   0.00149  -0.1019   0.8514   1.0000
   0.750   0.4995   0.00529   0.00146  -0.1014   0.8385   1.0000
   1.000   0.5254   0.00533   0.00146  -0.1008   0.8244   1.0000
   1.250   0.5514   0.00538   0.00146  -0.1002   0.8099   1.0000
   1.500   0.5773   0.00545   0.00148  -0.0997   0.7948   1.0000
   1.750   0.6028   0.00553   0.00151  -0.0991   0.7756   1.0000
   2.000   0.6277   0.00564   0.00154  -0.0983   0.7501   1.0000
   2.250   0.6516   0.00582   0.00161  -0.0973   0.7157   1.0000
   2.500   0.6723   0.00619   0.00168  -0.0956   0.6569   1.0000
   2.750   0.6947   0.00652   0.00183  -0.0944   0.6140   1.0000
   3.000   0.7168   0.00689   0.00201  -0.0932   0.5624   1.0000
   3.250   0.7314   0.00787   0.00230  -0.0907   0.4104   1.0000
   3.500   0.7334   0.01070   0.00341  -0.0868   0.0430   1.0000
   3.750   0.7558   0.01140   0.00414  -0.0856   0.0249   1.0000
   4.000   0.7795   0.01187   0.00467  -0.0847   0.0215   1.0000
   4.250   0.8022   0.01247   0.00530  -0.0837   0.0183   1.0000
   4.500   0.8198   0.01372   0.00667  -0.0817   0.0164   1.0000
   4.750   0.8387   0.01488   0.00793  -0.0799   0.0155   1.0000
   5.000   0.8597   0.01598   0.00909  -0.0784   0.0150   1.0000
   5.250   0.8813   0.01754   0.01077  -0.0770   0.0150   1.0000
   5.500   0.9055   0.01872   0.01203  -0.0761   0.0142   1.0000
   5.750   0.9301   0.01996   0.01337  -0.0753   0.0132   1.0000
   6.000   0.9557   0.02213   0.01573  -0.0744   0.0131   1.0000
   8.500   1.0389   0.04931   0.04626  -0.0474   0.0135   1.0000
   8.750   1.0335   0.05359   0.05075  -0.0446   0.0131   1.0000
   9.000   1.0223   0.05773   0.05506  -0.0415   0.0129   1.0000
   9.250   1.0027   0.06117   0.05864  -0.0376   0.0128   1.0000
   9.500   0.9799   0.06500   0.06259  -0.0349   0.0128   1.0000
   9.750   0.9545   0.06967   0.06738  -0.0337   0.0129   1.0000
  10.000   0.9279   0.07520   0.07304  -0.0341   0.0132   1.0000
  10.250   0.8999   0.08189   0.07984  -0.0364   0.0135   1.0000
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