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GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 375 AIRFOIL (goe375-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.89 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe375-il-1000000.txt
Download as CSV file: xf-goe375-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 375 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3747   0.10029   0.09870  -0.0076   1.0000   0.0081
  -8.500  -0.3704   0.09730   0.09573  -0.0091   1.0000   0.0082
  -8.250  -0.3651   0.09450   0.09293  -0.0099   1.0000   0.0082
  -8.000  -0.2805   0.07725   0.07582  -0.0157   1.0000   0.0084
  -7.750  -0.2779   0.07426   0.07284  -0.0158   1.0000   0.0085
  -7.500  -0.2770   0.07128   0.06988  -0.0161   1.0000   0.0086
  -7.250  -0.2774   0.06848   0.06710  -0.0161   1.0000   0.0087
  -7.000  -0.2807   0.06599   0.06465  -0.0156   1.0000   0.0088
  -6.750  -0.2848   0.06346   0.06216  -0.0153   1.0000   0.0089
  -6.250  -0.2558   0.05484   0.05352  -0.0248   0.9892   0.0093
  -6.000  -0.2318   0.04980   0.04846  -0.0313   0.9802   0.0096
  -5.750  -0.2014   0.04439   0.04298  -0.0390   0.9643   0.0101
  -5.500  -0.1654   0.03896   0.03743  -0.0471   0.9358   0.0108
  -5.250  -0.1427   0.03481   0.03304  -0.0508   0.8903   0.0109
  -5.000  -0.1237   0.03109   0.02912  -0.0525   0.8622   0.0109
  -4.750  -0.1091   0.02661   0.02449  -0.0535   0.8440   0.0111
  -4.500  -0.0926   0.02395   0.02172  -0.0540   0.8284   0.0113
  -4.250  -0.0726   0.02168   0.01935  -0.0546   0.8158   0.0119
  -4.000  -0.0499   0.01925   0.01678  -0.0553   0.8052   0.0127
  -3.750  -0.0199   0.01701   0.01432  -0.0558   0.7958   0.0140
  -3.500   0.0077   0.01476   0.01184  -0.0558   0.7865   0.0141
  -3.250   0.0319   0.01260   0.00949  -0.0557   0.7768   0.0141
  -3.000   0.0530   0.00969   0.00640  -0.0560   0.7666   0.0144
  -2.750   0.0751   0.00842   0.00502  -0.0561   0.7528   0.0147
  -2.500   0.0992   0.00741   0.00387  -0.0559   0.7368   0.0155
  -2.250   0.1299   0.00693   0.00305  -0.0546   0.7187   0.0177
   0.000   0.3659   0.01201   0.00574  -0.0522   0.4635   0.0249
   0.250   0.3928   0.01234   0.00585  -0.0516   0.4379   0.0276
   0.500   0.4196   0.01245   0.00576  -0.0511   0.4158   0.0281
   3.250   0.7035   0.00960   0.00221  -0.0460   0.2415   0.0454
   3.500   0.7296   0.00962   0.00220  -0.0456   0.2337   0.0411
   3.750   0.7560   0.00970   0.00223  -0.0452   0.2267   0.0368
   4.000   0.7822   0.00980   0.00232  -0.0449   0.2200   0.0358
   4.250   0.8085   0.00983   0.00234  -0.0445   0.2144   0.0358
   4.500   0.8344   0.00992   0.00239  -0.0441   0.2077   0.0373
   4.750   0.8609   0.00998   0.00246  -0.0438   0.2030   0.0390
   5.000   0.8870   0.01011   0.00257  -0.0435   0.1970   0.0407
   5.250   0.9131   0.01024   0.00270  -0.0432   0.1910   0.0430
   5.500   0.9393   0.01037   0.00282  -0.0429   0.1847   0.0457
   5.750   0.9848   0.00901   0.00323  -0.0477   0.1764   1.0000
   6.000   1.0098   0.00922   0.00340  -0.0472   0.1679   1.0000
   6.250   1.0349   0.00942   0.00357  -0.0467   0.1598   1.0000
   6.500   1.0595   0.00968   0.00378  -0.0461   0.1515   1.0000
   6.750   1.0846   0.00987   0.00398  -0.0457   0.1455   1.0000
   7.000   1.1089   0.01016   0.00423  -0.0451   0.1376   1.0000
   7.250   1.1338   0.01037   0.00445  -0.0446   0.1320   1.0000
   7.500   1.1579   0.01068   0.00472  -0.0441   0.1242   1.0000
   7.750   1.1825   0.01091   0.00495  -0.0436   0.1182   1.0000
   8.000   1.2064   0.01123   0.00526  -0.0430   0.1103   1.0000
   8.250   1.2297   0.01161   0.00558  -0.0424   0.0985   1.0000
   8.500   1.2428   0.01319   0.00668  -0.0404   0.0346   1.0000
   8.750   1.2604   0.01427   0.00768  -0.0389   0.0138   1.0000
   9.000   1.2827   0.01475   0.00825  -0.0381   0.0124   1.0000
   9.250   1.3038   0.01537   0.00894  -0.0372   0.0111   1.0000
   9.500   1.3220   0.01632   0.01004  -0.0357   0.0096   1.0000
   9.750   1.3434   0.01685   0.01062  -0.0349   0.0093   1.0000
  10.000   1.3639   0.01743   0.01128  -0.0339   0.0087   1.0000
  10.250   1.3832   0.01813   0.01207  -0.0327   0.0082   1.0000
  10.500   1.4022   0.01880   0.01279  -0.0317   0.0076   1.0000
  10.750   1.4180   0.01976   0.01386  -0.0301   0.0071   1.0000
  11.000   1.4247   0.02146   0.01575  -0.0274   0.0066   1.0000
  11.250   1.4380   0.02243   0.01681  -0.0256   0.0064   1.0000
  11.500   1.4519   0.02327   0.01775  -0.0239   0.0062   1.0000
  11.750   1.4602   0.02439   0.01897  -0.0215   0.0060   1.0000
  12.000   1.4644   0.02543   0.02012  -0.0184   0.0059   1.0000
  12.250   1.4656   0.02667   0.02146  -0.0152   0.0057   1.0000
  12.500   1.4681   0.02797   0.02285  -0.0126   0.0055   1.0000
  12.750   1.4652   0.02980   0.02480  -0.0102   0.0054   1.0000
  13.000   1.4618   0.03196   0.02708  -0.0086   0.0054   1.0000
  13.250   1.4579   0.03451   0.02975  -0.0078   0.0052   1.0000
  13.500   1.4564   0.03714   0.03249  -0.0076   0.0051   1.0000
  13.750   1.4551   0.04004   0.03548  -0.0080   0.0049   1.0000
  14.000   1.4459   0.04431   0.03989  -0.0093   0.0048   1.0000
  14.250   1.4363   0.04918   0.04489  -0.0114   0.0048   1.0000
  14.500   1.4233   0.05500   0.05085  -0.0144   0.0048   1.0000
  14.750   1.4103   0.06095   0.05693  -0.0173   0.0047   1.0000
  15.000   1.3894   0.06811   0.06423  -0.0206   0.0047   1.0000
  15.250   1.3734   0.07453   0.07075  -0.0235   0.0046   1.0000
  15.500   1.3522   0.08160   0.07795  -0.0265   0.0047   1.0000
  15.750   1.3342   0.08839   0.08484  -0.0294   0.0047   1.0000
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