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GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 744 AIRFOIL (goe744-il)
Reynolds number: 200,000
Max Cl/Cd: 56.84 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe744-il-200000.txt
Download as CSV file: xf-goe744-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 744 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1666   0.09689   0.09235  -0.0011   0.5690   0.0511
  -7.500  -0.1721   0.09458   0.09008  -0.0047   0.5670   0.0522
  -7.250  -0.1973   0.09289   0.08841  -0.0112   0.5657   0.0526
  -7.000  -0.1803   0.08915   0.08467  -0.0095   0.5631   0.0529
  -6.750  -0.1611   0.08613   0.08161  -0.0080   0.5606   0.0535
  -6.500  -0.1520   0.08384   0.07927  -0.0081   0.5584   0.0542
  -6.250  -0.1426   0.08136   0.07684  -0.0094   0.5557   0.0551
  -6.000  -0.1334   0.07880   0.07431  -0.0113   0.5528   0.0561
  -5.750  -0.1239   0.07612   0.07163  -0.0137   0.5500   0.0576
  -5.500  -0.1158   0.07238   0.06771  -0.0215   0.5480   0.0595
  -5.250  -0.1016   0.06965   0.06501  -0.0204   0.5454   0.0600
  -5.000  -0.0866   0.06731   0.06264  -0.0200   0.5429   0.0607
  -4.750  -0.0709   0.06509   0.06035  -0.0202   0.5406   0.0618
  -4.500  -0.0539   0.06286   0.05803  -0.0211   0.5383   0.0636
  -4.250  -0.0305   0.05906   0.05401  -0.0261   0.5355   0.0674
  -4.000  -0.0134   0.05693   0.05196  -0.0256   0.5321   0.0681
  -3.750   0.0054   0.05506   0.05009  -0.0255   0.5290   0.0694
  -3.500   0.0324   0.05219   0.04684  -0.0282   0.5265   0.0760
  -3.250   0.0494   0.05011   0.04480  -0.0274   0.5239   0.0769
  -3.000   0.0686   0.04853   0.04316  -0.0266   0.5215   0.0786
  -2.750   0.0952   0.04629   0.04048  -0.0277   0.5192   0.0862
  -2.500   0.1156   0.04450   0.03885  -0.0276   0.5156   0.0873
  -2.250   0.1454   0.04452   0.03841  -0.0278   0.5122   0.0968
  -2.000   0.1633   0.04122   0.03528  -0.0276   0.5090   0.0982
  -1.750   0.1845   0.03972   0.03379  -0.0270   0.5061   0.1001
  -1.500   0.2096   0.03869   0.03259  -0.0265   0.5036   0.1071
  -1.250   0.2317   0.03685   0.03054  -0.0258   0.5014   0.1131
  -1.000   0.2578   0.03627   0.02973  -0.0256   0.4982   0.1256
  -0.750   0.2802   0.03484   0.02845  -0.0254   0.4941   0.1284
  -0.500   0.3052   0.03406   0.02751  -0.0250   0.4906   0.1425
  -0.250   0.3367   0.02705   0.01920  -0.0222   0.4885   0.0777
   0.000   0.3649   0.02557   0.01736  -0.0213   0.4859   0.0721
   0.250   0.3937   0.02434   0.01575  -0.0206   0.4837   0.0695
   0.500   0.4221   0.02376   0.01494  -0.0202   0.4811   0.0692
   0.750   0.4494   0.02357   0.01484  -0.0205   0.4763   0.0711
   1.000   0.4776   0.02320   0.01442  -0.0204   0.4725   0.0729
   1.250   0.5062   0.02270   0.01383  -0.0201   0.4694   0.0740
   1.500   0.5348   0.02223   0.01325  -0.0197   0.4669   0.0753
   1.750   0.5625   0.02168   0.01267  -0.0192   0.4647   0.0778
   2.000   0.5880   0.02176   0.01289  -0.0190   0.4606   0.0820
   2.250   0.6131   0.02173   0.01296  -0.0187   0.4561   0.0874
   2.500   0.6391   0.02153   0.01279  -0.0182   0.4527   0.0944
   2.750   0.6654   0.02118   0.01244  -0.0175   0.4500   0.1081
   3.000   0.6893   0.02057   0.01222  -0.0163   0.4478   0.2339
   3.250   0.8613   0.01939   0.01263  -0.0452   0.4399   1.0000
   3.500   0.8865   0.01952   0.01268  -0.0447   0.4361   1.0000
   3.750   0.9121   0.01950   0.01254  -0.0441   0.4332   1.0000
   4.000   0.9379   0.01943   0.01231  -0.0434   0.4308   1.0000
   4.250   0.9629   0.01967   0.01245  -0.0428   0.4279   1.0000
   4.500   0.9860   0.02023   0.01312  -0.0428   0.4228   1.0000
   4.750   1.0105   0.02038   0.01324  -0.0423   0.4190   1.0000
   5.000   1.0360   0.02033   0.01309  -0.0417   0.4161   1.0000
   5.250   1.0621   0.02023   0.01285  -0.0410   0.4135   1.0000
   5.500   1.0850   0.02068   0.01332  -0.0406   0.4097   1.0000
   5.750   1.1069   0.02119   0.01391  -0.0403   0.4050   1.0000
   6.000   1.1310   0.02134   0.01403  -0.0397   0.4016   1.0000
   6.250   1.1564   0.02132   0.01391  -0.0391   0.3988   1.0000
   6.500   1.1826   0.02130   0.01375  -0.0385   0.3963   1.0000
   6.750   1.2009   0.02208   0.01470  -0.0380   0.3913   1.0000
   7.000   1.2222   0.02244   0.01509  -0.0374   0.3870   1.0000
   7.250   1.2466   0.02247   0.01506  -0.0368   0.3838   1.0000
   7.500   1.2727   0.02243   0.01491  -0.0362   0.3810   1.0000
   7.750   1.2917   0.02307   0.01561  -0.0355   0.3772   1.0000
   8.000   1.3079   0.02381   0.01645  -0.0347   0.3727   1.0000
   8.250   1.3293   0.02409   0.01672  -0.0339   0.3691   1.0000
   8.500   1.3540   0.02415   0.01671  -0.0334   0.3663   1.0000
   8.750   1.3801   0.02428   0.01672  -0.0329   0.3634   1.0000
   9.000   1.3858   0.02552   0.01819  -0.0313   0.3586   1.0000
   9.250   1.4011   0.02611   0.01882  -0.0302   0.3547   1.0000
   9.500   1.4233   0.02627   0.01895  -0.0295   0.3515   1.0000
   9.750   1.4504   0.02631   0.01888  -0.0291   0.3488   1.0000
  10.000   1.4564   0.02750   0.02019  -0.0274   0.3452   1.0000
  10.250   1.4537   0.02897   0.02180  -0.0250   0.3412   1.0000
  10.500   1.4628   0.02981   0.02269  -0.0235   0.3379   1.0000
  10.750   1.4855   0.02998   0.02281  -0.0228   0.3352   1.0000
  11.000   1.5209   0.02975   0.02246  -0.0231   0.3327   1.0000
  11.250   1.4817   0.03268   0.02559  -0.0183   0.3290   1.0000
  11.500   1.4414   0.03679   0.02989  -0.0156   0.3242   1.0000
  11.750   1.4544   0.03762   0.03072  -0.0148   0.3213   1.0000
  12.000   1.4858   0.03717   0.03023  -0.0144   0.3192   1.0000
  12.250   1.5279   0.03621   0.02919  -0.0143   0.3173   1.0000
  12.500   1.3040   0.05898   0.05251  -0.0137   0.3037   1.0000
  12.750   1.3527   0.05602   0.04951  -0.0127   0.3035   1.0000
  13.000   1.4085   0.05250   0.04595  -0.0117   0.3033   1.0000
  13.250   1.4578   0.04997   0.04336  -0.0109   0.3025   1.0000
  13.500   1.5094   0.04756   0.04089  -0.0103   0.3015   1.0000
  13.750   0.7859   0.15983   0.15412  -0.0424   0.2623   1.0000
  14.000   0.8028   0.16092   0.15522  -0.0421   0.2594   1.0000
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