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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.98 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe401-il-1000000-n5.txt
Download as CSV file: xf-goe401-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3584   0.09569   0.09404  -0.0195   1.0000   0.0104
  -8.750  -0.3555   0.09294   0.09130  -0.0201   1.0000   0.0108
  -8.500  -0.3583   0.08597   0.08434  -0.0251   0.9986   0.0120
  -8.250  -0.3430   0.08356   0.08194  -0.0279   0.9931   0.0122
  -8.000  -0.3364   0.08103   0.07942  -0.0295   0.9811   0.0123
  -7.750  -0.3067   0.07718   0.07554  -0.0369   0.9481   0.0125
  -7.500  -0.2396   0.07080   0.06906  -0.0551   0.9278   0.0132
  -7.250  -0.1936   0.06072   0.05866  -0.0749   0.8783   0.0150
  -7.000  -0.1796   0.05886   0.05662  -0.0762   0.8405   0.0152
  -6.750  -0.1673   0.05670   0.05432  -0.0773   0.8114   0.0153
  -6.500  -0.1525   0.05470   0.05222  -0.0784   0.7900   0.0155
  -6.250  -0.1366   0.05241   0.04983  -0.0798   0.7726   0.0158
  -6.000  -0.1197   0.04976   0.04708  -0.0815   0.7571   0.0161
  -5.750  -0.1015   0.04699   0.04420  -0.0832   0.7429   0.0166
  -5.500  -0.0824   0.04296   0.04003  -0.0856   0.7302   0.0175
  -5.250  -0.0641   0.03502   0.03177  -0.0890   0.7195   0.0186
  -5.000  -0.0423   0.03337   0.03000  -0.0893   0.7065   0.0188
  -4.750  -0.0197   0.03184   0.02835  -0.0895   0.6949   0.0191
  -4.500   0.0033   0.03053   0.02694  -0.0895   0.6819   0.0193
  -4.250   0.0259   0.02832   0.02456  -0.0895   0.6692   0.0197
  -4.000   0.0485   0.02580   0.02183  -0.0893   0.6549   0.0200
  -3.750   0.0612   0.01536   0.01045  -0.0876   0.6474   0.0211
  -3.500   0.0838   0.01362   0.00831  -0.0867   0.6323   0.0215
  -3.250   0.1081   0.01273   0.00716  -0.0859   0.6147   0.0218
  -3.000   0.1328   0.01216   0.00636  -0.0852   0.5936   0.0221
  -2.750   0.1579   0.01180   0.00580  -0.0845   0.5685   0.0223
  -2.500   0.1830   0.01151   0.00533  -0.0839   0.5425   0.0224
  -2.250   0.2081   0.01134   0.00497  -0.0832   0.5123   0.0226
  -2.000   0.2332   0.01115   0.00460  -0.0825   0.4848   0.0227
  -1.750   0.2580   0.01059   0.00386  -0.0819   0.4653   0.0229
  -1.500   0.2833   0.01022   0.00337  -0.0813   0.4503   0.0231
  -1.250   0.3089   0.00996   0.00303  -0.0807   0.4375   0.0233
  -1.000   0.3350   0.00976   0.00276  -0.0802   0.4279   0.0235
  -0.750   0.3610   0.00959   0.00255  -0.0797   0.4192   0.0237
  -0.500   0.3872   0.00946   0.00237  -0.0792   0.4114   0.0240
  -0.250   0.4134   0.00938   0.00226  -0.0788   0.4044   0.0245
   0.000   0.4397   0.00925   0.00211  -0.0783   0.3983   0.0247
   0.250   0.4658   0.00916   0.00198  -0.0778   0.3920   0.0251
   0.500   0.4922   0.00906   0.00187  -0.0774   0.3872   0.0254
   0.750   0.5185   0.00899   0.00178  -0.0769   0.3814   0.0259
   1.000   0.5447   0.00896   0.00172  -0.0765   0.3759   0.0265
   1.250   0.5712   0.00891   0.00167  -0.0761   0.3716   0.0269
   1.500   0.5977   0.00889   0.00164  -0.0757   0.3658   0.0274
   1.750   0.6240   0.00890   0.00163  -0.0752   0.3603   0.0278
   2.000   0.6505   0.00890   0.00162  -0.0749   0.3558   0.0280
   2.250   0.6769   0.00889   0.00162  -0.0745   0.3503   0.0284
   2.500   0.7030   0.00892   0.00161  -0.0740   0.3443   0.0293
   2.750   0.7296   0.00892   0.00163  -0.0736   0.3400   0.0310
   3.000   0.7559   0.00896   0.00166  -0.0732   0.3344   0.0328
   3.250   0.7820   0.00903   0.00171  -0.0728   0.3261   0.0349
   3.500   0.8074   0.00908   0.00179  -0.0723   0.3145   0.0663
   3.750   0.8331   0.00913   0.00189  -0.0718   0.3036   0.1032
   4.000   0.8587   0.00919   0.00202  -0.0714   0.2960   0.1435
   4.250   0.8845   0.00927   0.00214  -0.0709   0.2878   0.1707
   4.500   0.9089   0.00921   0.00229  -0.0703   0.2793   0.3097
   5.000   1.0021   0.00844   0.00280  -0.0796   0.2487   1.0000
   5.250   1.0263   0.00864   0.00296  -0.0788   0.2393   1.0000
   5.500   1.0506   0.00883   0.00312  -0.0781   0.2300   1.0000
   5.750   1.0738   0.00911   0.00332  -0.0772   0.2143   1.0000
   6.000   1.0971   0.00938   0.00353  -0.0764   0.2008   1.0000
   6.250   1.1198   0.00971   0.00377  -0.0754   0.1842   1.0000
   6.500   1.1415   0.01012   0.00406  -0.0743   0.1623   1.0000
   6.750   1.1621   0.01062   0.00442  -0.0731   0.1357   1.0000
   7.000   1.1745   0.01184   0.00524  -0.0706   0.0659   1.0000
   7.250   1.1962   0.01224   0.00559  -0.0695   0.0570   1.0000
   7.500   1.2185   0.01257   0.00592  -0.0685   0.0506   1.0000
   7.750   1.2409   0.01288   0.00624  -0.0676   0.0466   1.0000
   8.000   1.2626   0.01326   0.00660  -0.0666   0.0419   1.0000
   8.250   1.2847   0.01357   0.00692  -0.0656   0.0379   1.0000
   8.500   1.3051   0.01403   0.00732  -0.0644   0.0295   1.0000
   8.750   1.3233   0.01465   0.00786  -0.0629   0.0178   1.0000
   9.000   1.3433   0.01510   0.00831  -0.0616   0.0148   1.0000
   9.250   1.3633   0.01554   0.00877  -0.0604   0.0132   1.0000
   9.500   1.3824   0.01603   0.00929  -0.0590   0.0117   1.0000
   9.750   1.4021   0.01645   0.00975  -0.0577   0.0110   1.0000
  10.000   1.4211   0.01690   0.01023  -0.0564   0.0102   1.0000
  10.250   1.4390   0.01740   0.01076  -0.0549   0.0095   1.0000
  10.500   1.4558   0.01795   0.01135  -0.0532   0.0090   1.0000
  10.750   1.4712   0.01855   0.01200  -0.0514   0.0084   1.0000
  11.000   1.4873   0.01907   0.01258  -0.0496   0.0081   1.0000
  11.250   1.5004   0.01960   0.01316  -0.0473   0.0078   1.0000
  11.500   1.5121   0.02017   0.01379  -0.0449   0.0075   1.0000
  11.750   1.5232   0.02081   0.01447  -0.0424   0.0071   1.0000
  12.000   1.5333   0.02154   0.01525  -0.0400   0.0068   1.0000
  12.250   1.5429   0.02233   0.01609  -0.0377   0.0065   1.0000
  12.500   1.5502   0.02331   0.01714  -0.0353   0.0062   1.0000
  12.750   1.5563   0.02443   0.01834  -0.0331   0.0060   1.0000
  13.000   1.5638   0.02555   0.01953  -0.0312   0.0059   1.0000
  13.250   1.5707   0.02680   0.02087  -0.0296   0.0058   1.0000
  13.500   1.5769   0.02821   0.02236  -0.0282   0.0056   1.0000
  13.750   1.5816   0.02984   0.02408  -0.0269   0.0055   1.0000
  14.000   1.5858   0.03165   0.02598  -0.0260   0.0053   1.0000
  14.250   1.5879   0.03377   0.02820  -0.0252   0.0052   1.0000
  14.500   1.5886   0.03619   0.03071  -0.0246   0.0052   1.0000
  14.750   1.5893   0.03871   0.03332  -0.0244   0.0051   1.0000
  15.000   1.5885   0.04152   0.03623  -0.0243   0.0049   1.0000
  15.250   1.5859   0.04467   0.03947  -0.0245   0.0048   1.0000
  15.500   1.5798   0.04837   0.04328  -0.0250   0.0048   1.0000
  15.750   1.5734   0.05226   0.04728  -0.0257   0.0047   1.0000
  16.000   1.5642   0.05666   0.05179  -0.0267   0.0047   1.0000
  16.250   1.5523   0.06158   0.05682  -0.0280   0.0046   1.0000
  16.500   1.5408   0.06657   0.06191  -0.0294   0.0044   1.0000
  16.750   1.5274   0.07190   0.06736  -0.0310   0.0045   1.0000
  17.000   1.5151   0.07710   0.07267  -0.0325   0.0045   1.0000
  17.250   1.4991   0.08293   0.07861  -0.0344   0.0043   1.0000
  17.500   1.4850   0.08847   0.08426  -0.0361   0.0043   1.0000
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