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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 500,000
Max Cl/Cd: 108.58 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe372-il-500000.txt
Download as CSV file: xf-goe372-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 372 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3537   0.10033   0.09810  -0.0293   1.0000   0.0183
  -8.500  -0.3518   0.09746   0.09526  -0.0300   1.0000   0.0184
  -8.250  -0.3510   0.09460   0.09243  -0.0303   1.0000   0.0184
  -8.000  -0.2919   0.07606   0.07410  -0.0325   1.0000   0.0191
  -7.750  -0.2902   0.07383   0.07190  -0.0305   1.0000   0.0197
  -7.500  -0.2912   0.07264   0.07075  -0.0279   1.0000   0.0205
  -7.250  -0.2823   0.06909   0.06721  -0.0302   0.9979   0.0213
  -7.000  -0.2682   0.06449   0.06260  -0.0349   0.9939   0.0222
  -6.750  -0.2539   0.05975   0.05787  -0.0403   0.9875   0.0232
  -5.750  -0.2074   0.04545   0.04314  -0.0791   0.9741   0.0179
  -5.500  -0.1639   0.01886   0.01500  -0.0991   0.9668   0.0183
  -5.250  -0.1341   0.01588   0.01154  -0.1009   0.9609   0.0212
  -5.000  -0.0984   0.01547   0.01103  -0.1026   0.9572   0.0241
  -4.750  -0.0675   0.01467   0.00998  -0.1032   0.9498   0.0267
  -4.500  -0.0367   0.01273   0.00768  -0.1043   0.9434   0.0311
  -4.250  -0.0068   0.01265   0.00754  -0.1046   0.9346   0.0350
  -4.000   0.0245   0.01209   0.00678  -0.1052   0.9273   0.0375
  -3.750   0.0521   0.01108   0.00552  -0.1052   0.9171   0.0398
  -3.500   0.0795   0.01039   0.00472  -0.1050   0.9068   0.0426
  -3.250   0.1075   0.01006   0.00429  -0.1049   0.8970   0.0453
  -3.000   0.1352   0.00973   0.00382  -0.1047   0.8874   0.0481
  -2.750   0.1619   0.00941   0.00340  -0.1043   0.8767   0.0497
  -2.500   0.1883   0.00899   0.00287  -0.1039   0.8668   0.0514
  -2.250   0.2148   0.00863   0.00247  -0.1035   0.8577   0.0550
  -2.000   0.2416   0.00848   0.00226  -0.1031   0.8482   0.0595
  -1.750   0.2681   0.00828   0.00204  -0.1027   0.8388   0.0692
  -1.500   0.2950   0.00818   0.00191  -0.1024   0.8302   0.0840
  -1.250   0.3216   0.00809   0.00179  -0.1020   0.8212   0.0941
  -1.000   0.3484   0.00804   0.00172  -0.1017   0.8125   0.1022
  -0.750   0.3751   0.00796   0.00161  -0.1013   0.8041   0.1103
  -0.500   0.4017   0.00791   0.00155  -0.1010   0.7947   0.1186
  -0.250   0.4283   0.00784   0.00149  -0.1006   0.7856   0.1309
   0.000   0.4546   0.00777   0.00145  -0.1002   0.7759   0.1496
   0.250   0.4805   0.00763   0.00143  -0.0998   0.7646   0.1920
   0.500   0.5055   0.00730   0.00147  -0.0993   0.7530   0.3285
   0.750   0.5508   0.00581   0.00153  -0.1035   0.7423   1.0000
   1.000   0.5767   0.00589   0.00153  -0.1030   0.7308   1.0000
   1.250   0.6024   0.00597   0.00154  -0.1024   0.7175   1.0000
   1.500   0.6281   0.00606   0.00156  -0.1018   0.7033   1.0000
   1.750   0.6536   0.00615   0.00159  -0.1012   0.6875   1.0000
   2.000   0.6786   0.00627   0.00162  -0.1005   0.6673   1.0000
   2.250   0.7014   0.00646   0.00163  -0.0993   0.6251   1.0000
   2.500   0.7236   0.00675   0.00170  -0.0980   0.5777   1.0000
   2.750   0.7463   0.00707   0.00182  -0.0969   0.5414   1.0000
   3.000   0.7690   0.00743   0.00198  -0.0959   0.5018   1.0000
   3.250   0.7898   0.00794   0.00216  -0.0945   0.4309   1.0000
   3.500   0.8006   0.00956   0.00275  -0.0918   0.2238   1.0000
   3.750   0.8121   0.01132   0.00362  -0.0893   0.0313   1.0000
   4.000   0.8364   0.01168   0.00397  -0.0885   0.0218   1.0000
   4.250   0.8605   0.01204   0.00441  -0.0877   0.0196   1.0000
   4.500   0.8839   0.01249   0.00495  -0.0868   0.0177   1.0000
   4.750   0.9062   0.01307   0.00561  -0.0856   0.0163   1.0000
   5.000   0.9269   0.01384   0.00650  -0.0841   0.0154   1.0000
   5.250   0.9461   0.01474   0.00749  -0.0824   0.0151   1.0000
   5.500   0.9654   0.01559   0.00841  -0.0808   0.0152   1.0000
   5.750   0.9849   0.01646   0.00933  -0.0791   0.0156   1.0000
   6.000   0.9999   0.01801   0.01092  -0.0769   0.0147   1.0000
   6.250   1.0195   0.01927   0.01221  -0.0753   0.0147   1.0000
   6.500   1.0421   0.02025   0.01325  -0.0740   0.0154   1.0000
   7.000   1.0963   0.02477   0.01810  -0.0721   0.0206   1.0000
   7.250   1.1192   0.02609   0.01956  -0.0710   0.0189   1.0000
   7.500   1.1409   0.02779   0.02139  -0.0699   0.0174   1.0000
   7.750   1.1620   0.02981   0.02350  -0.0689   0.0163   1.0000
   8.000   1.1823   0.03227   0.02606  -0.0680   0.0154   1.0000
  11.750   1.1339   0.07694   0.07408  -0.0333   0.0101   1.0000
  12.000   1.1136   0.08257   0.07986  -0.0353   0.0102   1.0000
  12.250   1.0922   0.08911   0.08655  -0.0385   0.0103   1.0000
  12.500   1.0694   0.09692   0.09450  -0.0432   0.0105   1.0000
  12.750   1.0444   0.10654   0.10426  -0.0497   0.0108   1.0000
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