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GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 746 AIRFOIL (goe746-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.59 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe746-il-1000000-n5.txt
Download as CSV file: xf-goe746-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 746 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4398   0.09439   0.09140   0.0167   0.5127   0.0063
  -8.500  -0.4483   0.08913   0.08617   0.0143   0.5113   0.0066
  -8.250  -0.4493   0.08601   0.08308   0.0127   0.5095   0.0067
  -8.000  -0.4507   0.08344   0.08053   0.0116   0.5074   0.0068
  -7.750  -0.4453   0.08071   0.07779   0.0098   0.5050   0.0069
  -7.500  -0.4396   0.07714   0.07421   0.0073   0.5027   0.0070
  -7.250  -0.4308   0.07372   0.07076   0.0049   0.5001   0.0073
  -7.000  -0.4212   0.06980   0.06680   0.0022   0.4976   0.0076
  -6.750  -0.4202   0.06069   0.05758  -0.0034   0.4967   0.0089
  -6.500  -0.4029   0.05762   0.05446  -0.0051   0.4946   0.0091
  -6.250  -0.3840   0.05484   0.05161  -0.0066   0.4926   0.0093
  -6.000  -0.3644   0.05189   0.04858  -0.0080   0.4903   0.0096
  -5.750  -0.3447   0.04825   0.04483  -0.0094   0.4880   0.0102
  -5.500  -0.3297   0.03926   0.03553  -0.0115   0.4865   0.0119
  -5.000  -0.2981   0.02444   0.01978  -0.0102   0.4830   0.0152
  -4.750  -0.2721   0.02405   0.01932  -0.0100   0.4802   0.0154
  -4.500  -0.2458   0.02372   0.01895  -0.0099   0.4780   0.0156
  -4.250  -0.2203   0.02290   0.01803  -0.0096   0.4756   0.0160
  -4.000  -0.1956   0.02143   0.01638  -0.0091   0.4733   0.0165
  -3.750  -0.1749   0.01681   0.01107  -0.0072   0.4712   0.0190
  -3.500  -0.1497   0.01543   0.00942  -0.0067   0.4685   0.0195
  -3.250  -0.1231   0.01490   0.00880  -0.0064   0.4657   0.0198
  -3.000  -0.0958   0.01461   0.00848  -0.0063   0.4637   0.0201
  -2.750  -0.0687   0.01412   0.00789  -0.0060   0.4615   0.0204
  -2.500  -0.0415   0.01357   0.00726  -0.0058   0.4591   0.0207
  -2.250  -0.0141   0.01305   0.00664  -0.0055   0.4564   0.0209
  -2.000   0.0133   0.01254   0.00602  -0.0053   0.4536   0.0213
  -1.500   0.0687   0.01173   0.00506  -0.0049   0.4490   0.0222
  -1.250   0.0964   0.01129   0.00456  -0.0047   0.4468   0.0226
  -1.000   0.1242   0.01093   0.00414  -0.0046   0.4442   0.0230
  -0.750   0.1520   0.01064   0.00380  -0.0044   0.4413   0.0234
  -0.500   0.1797   0.01040   0.00351  -0.0043   0.4386   0.0238
  -0.250   0.2075   0.01019   0.00326  -0.0041   0.4359   0.0240
   0.000   0.2353   0.00997   0.00303  -0.0040   0.4337   0.0242
   0.250   0.2630   0.00978   0.00283  -0.0039   0.4310   0.0243
   0.500   0.2907   0.00961   0.00264  -0.0037   0.4281   0.0244
   0.750   0.3183   0.00944   0.00246  -0.0036   0.4251   0.0245
   1.000   0.3455   0.00925   0.00224  -0.0034   0.4215   0.0248
   1.250   0.3725   0.00898   0.00197  -0.0031   0.4179   0.0254
   1.500   0.4000   0.00884   0.00182  -0.0030   0.4127   0.0256
   1.750   0.4274   0.00875   0.00169  -0.0028   0.4078   0.0261
   2.000   0.4551   0.00867   0.00162  -0.0027   0.4046   0.0266
   2.250   0.4829   0.00861   0.00156  -0.0027   0.4009   0.0274
   2.500   0.5106   0.00858   0.00153  -0.0026   0.3968   0.0283
   2.750   0.5384   0.00858   0.00152  -0.0026   0.3928   0.0290
   3.000   0.5663   0.00857   0.00152  -0.0026   0.3892   0.0298
   3.250   0.5941   0.00857   0.00153  -0.0026   0.3848   0.0304
   3.500   0.6219   0.00860   0.00155  -0.0026   0.3804   0.0310
   3.750   0.6497   0.00863   0.00158  -0.0026   0.3763   0.0316
   4.000   0.6776   0.00866   0.00162  -0.0026   0.3718   0.0333
   4.250   0.7053   0.00871   0.00168  -0.0027   0.3657   0.0373
   4.500   0.7271   0.00808   0.00190  -0.0018   0.3596   0.4727
   5.000   0.8142   0.00722   0.00229  -0.0089   0.3431   0.9878
   5.250   0.8513   0.00738   0.00242  -0.0110   0.3355   0.9905
   5.500   0.8868   0.00757   0.00257  -0.0129   0.3238   0.9935
   5.750   0.9345   0.00788   0.00277  -0.0176   0.3007   0.9972
   6.000   0.9651   0.00823   0.00302  -0.0186   0.2774   0.9981
   6.250   0.9932   0.00858   0.00327  -0.0192   0.2572   0.9986
   6.500   1.0211   0.00902   0.00360  -0.0197   0.2343   0.9991
   6.750   1.0493   0.00942   0.00391  -0.0203   0.2154   0.9996
   7.000   1.0760   0.01007   0.00440  -0.0209   0.1833   1.0000
   7.250   1.0986   0.01071   0.00488  -0.0206   0.1555   1.0000
   7.500   1.1144   0.01250   0.00621  -0.0202   0.0749   1.0000
   7.750   1.1306   0.01395   0.00741  -0.0195   0.0181   1.0000
   8.000   1.1523   0.01441   0.00788  -0.0189   0.0148   1.0000
   8.250   1.1737   0.01487   0.00837  -0.0183   0.0124   1.0000
   8.500   1.1950   0.01530   0.00883  -0.0177   0.0116   1.0000
   8.750   1.2155   0.01579   0.00935  -0.0170   0.0105   1.0000
   9.000   1.2348   0.01637   0.00996  -0.0163   0.0094   1.0000
   9.250   1.2531   0.01700   0.01063  -0.0155   0.0085   1.0000
   9.500   1.2713   0.01760   0.01127  -0.0147   0.0081   1.0000
   9.750   1.2883   0.01827   0.01198  -0.0139   0.0076   1.0000
  10.000   1.3035   0.01905   0.01281  -0.0130   0.0072   1.0000
  10.250   1.3164   0.02005   0.01387  -0.0123   0.0068   1.0000
  10.500   1.3223   0.02170   0.01558  -0.0119   0.0064   1.0000
  10.750   1.3178   0.02368   0.01763  -0.0103   0.0061   1.0000
  11.000   1.3209   0.02553   0.01955  -0.0096   0.0060   1.0000
  11.250   1.3274   0.02723   0.02130  -0.0092   0.0057   1.0000
  11.500   1.3323   0.02914   0.02328  -0.0090   0.0055   1.0000
  11.750   1.3351   0.03134   0.02554  -0.0088   0.0054   1.0000
  12.000   1.3389   0.03346   0.02772  -0.0086   0.0051   1.0000
  12.250   1.3410   0.03579   0.03013  -0.0086   0.0050   1.0000
  12.500   1.3415   0.03831   0.03270  -0.0086   0.0048   1.0000
  12.750   1.3412   0.04092   0.03538  -0.0086   0.0047   1.0000
  13.000   1.3411   0.04354   0.03806  -0.0087   0.0045   1.0000
  13.250   1.3416   0.04609   0.04068  -0.0087   0.0045   1.0000
  13.500   1.3382   0.04918   0.04383  -0.0090   0.0044   1.0000
  13.750   1.3318   0.05274   0.04747  -0.0094   0.0042   1.0000
  14.000   1.3279   0.05609   0.05090  -0.0099   0.0040   1.0000
  14.250   1.3228   0.05970   0.05460  -0.0105   0.0041   1.0000
  14.500   1.3229   0.06267   0.05764  -0.0109   0.0040   1.0000
  14.750   1.3196   0.06616   0.06120  -0.0116   0.0039   1.0000
  15.000   1.3155   0.06978   0.06491  -0.0123   0.0039   1.0000
  15.250   1.3143   0.07308   0.06828  -0.0129   0.0038   1.0000
  15.500   1.3085   0.07708   0.07237  -0.0138   0.0037   1.0000
  15.750   1.3062   0.08057   0.07593  -0.0146   0.0036   1.0000
  16.000   1.3028   0.08433   0.07976  -0.0155   0.0035   1.0000
  16.250   1.2963   0.08855   0.08407  -0.0166   0.0035   1.0000
  16.500   1.2922   0.09247   0.08806  -0.0176   0.0035   1.0000
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