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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 1,000,000
Max Cl/Cd: 89.64 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe372-il-1000000-n5.txt
Download as CSV file: xf-goe372-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3886   0.09291   0.09138  -0.0275   1.0000   0.0026
  -8.750  -0.3923   0.08900   0.08750  -0.0283   1.0000   0.0026
  -8.500  -0.4047   0.08420   0.08274  -0.0287   1.0000   0.0027
  -8.250  -0.3970   0.07889   0.07745  -0.0343   0.9950   0.0028
  -8.000  -0.4009   0.05906   0.05753  -0.0601   0.9789   0.0028
  -7.750  -0.3798   0.01984   0.01692  -0.1019   0.9596   0.0025
  -7.500  -0.3522   0.01648   0.01314  -0.1039   0.9513   0.0025
  -7.250  -0.3251   0.01419   0.01046  -0.1050   0.9398   0.0027
  -7.000  -0.2980   0.01296   0.00897  -0.1053   0.9253   0.0029
  -6.750  -0.2716   0.01222   0.00805  -0.1053   0.9089   0.0032
  -6.500  -0.2458   0.01157   0.00721  -0.1051   0.8924   0.0036
  -6.250  -0.2203   0.01099   0.00642  -0.1047   0.8764   0.0039
  -6.000  -0.1948   0.01050   0.00574  -0.1043   0.8610   0.0042
  -5.750  -0.1695   0.00992   0.00492  -0.1038   0.8463   0.0046
  -5.500  -0.1440   0.00940   0.00423  -0.1033   0.8326   0.0054
  -5.250  -0.1180   0.00904   0.00373  -0.1029   0.8210   0.0062
  -5.000  -0.0918   0.00877   0.00332  -0.1025   0.8098   0.0069
  -4.750  -0.0657   0.00838   0.00287  -0.1021   0.7994   0.0102
  -4.500  -0.0393   0.00811   0.00260  -0.1019   0.7906   0.0192
  -4.250  -0.0124   0.00796   0.00237  -0.1016   0.7829   0.0221
  -4.000   0.0144   0.00783   0.00221  -0.1014   0.7752   0.0272
  -3.750   0.0416   0.00776   0.00208  -0.1012   0.7676   0.0302
  -3.500   0.0686   0.00772   0.00197  -0.1010   0.7601   0.0318
  -3.250   0.0960   0.00772   0.00193  -0.1009   0.7531   0.0324
  -3.000   0.1228   0.00752   0.00165  -0.1006   0.7460   0.0339
  -2.750   0.1499   0.00738   0.00145  -0.1004   0.7389   0.0350
  -2.500   0.1768   0.00728   0.00128  -0.1001   0.7314   0.0361
  -2.250   0.2041   0.00719   0.00114  -0.0999   0.7240   0.0372
  -2.000   0.2310   0.00712   0.00103  -0.0997   0.7165   0.0385
  -1.750   0.2582   0.00704   0.00093  -0.0995   0.7083   0.0402
  -1.500   0.2852   0.00699   0.00084  -0.0993   0.7001   0.0436
  -1.250   0.3121   0.00691   0.00079  -0.0991   0.6901   0.0558
  -1.000   0.3390   0.00688   0.00076  -0.0988   0.6782   0.0671
  -0.750   0.3657   0.00689   0.00071  -0.0985   0.6627   0.0705
  -0.500   0.3921   0.00690   0.00068  -0.0982   0.6452   0.0760
  -0.250   0.4186   0.00694   0.00066  -0.0979   0.6249   0.0806
   0.000   0.4447   0.00701   0.00064  -0.0975   0.6009   0.0833
   0.250   0.4706   0.00709   0.00065  -0.0971   0.5770   0.0890
   0.500   0.4966   0.00718   0.00068  -0.0968   0.5558   0.0953
   0.750   0.5229   0.00724   0.00072  -0.0965   0.5396   0.1059
   1.000   0.5491   0.00730   0.00077  -0.0961   0.5241   0.1241
   1.250   0.5752   0.00735   0.00083  -0.0958   0.5083   0.1472
   1.500   0.6011   0.00740   0.00091  -0.0955   0.4916   0.1797
   1.750   0.6259   0.00748   0.00102  -0.0950   0.4599   0.2436
   2.000   0.6514   0.00748   0.00112  -0.0947   0.4378   0.3161
   2.250   0.6759   0.00754   0.00125  -0.0941   0.4055   0.4060
   2.750   0.7256   0.00833   0.00216  -0.0945   0.1353   1.0000
   3.000   0.7445   0.00927   0.00264  -0.0930   0.0167   1.0000
   3.250   0.7700   0.00947   0.00284  -0.0925   0.0121   1.0000
   3.500   0.7954   0.00967   0.00307  -0.0920   0.0099   1.0000
   3.750   0.8206   0.00989   0.00331  -0.0915   0.0082   1.0000
   4.000   0.8453   0.01017   0.00361  -0.0909   0.0070   1.0000
   4.250   0.8692   0.01056   0.00405  -0.0901   0.0060   1.0000
   4.500   0.8939   0.01081   0.00433  -0.0895   0.0052   1.0000
   4.750   0.9182   0.01112   0.00465  -0.0889   0.0046   1.0000
   5.000   0.9418   0.01150   0.00505  -0.0881   0.0042   1.0000
   5.250   0.9635   0.01211   0.00572  -0.0870   0.0037   1.0000
   5.500   0.9858   0.01264   0.00632  -0.0859   0.0034   1.0000
   5.750   1.0067   0.01332   0.00709  -0.0846   0.0033   1.0000
   6.000   1.0261   0.01414   0.00800  -0.0830   0.0031   1.0000
   6.250   1.0461   0.01488   0.00880  -0.0816   0.0028   1.0000
   6.500   1.0693   0.01520   0.00914  -0.0810   0.0026   1.0000
   6.750   1.0896   0.01586   0.00985  -0.0798   0.0024   1.0000
   7.000   1.1087   0.01666   0.01070  -0.0784   0.0023   1.0000
   7.250   1.1229   0.01822   0.01238  -0.0760   0.0021   1.0000
   7.500   1.1409   0.01952   0.01379  -0.0743   0.0021   1.0000
   7.750   1.1594   0.02178   0.01624  -0.0724   0.0019   1.0000
   8.000   1.1808   0.02486   0.01953  -0.0709   0.0016   1.0000
   8.250   1.2003   0.02785   0.02278  -0.0691   0.0015   1.0000
   8.500   1.2164   0.03083   0.02603  -0.0671   0.0015   1.0000
   8.750   1.2292   0.03422   0.02973  -0.0645   0.0015   1.0000
   9.000   1.2387   0.03738   0.03316  -0.0618   0.0016   1.0000
   9.250   1.2442   0.04090   0.03697  -0.0586   0.0016   1.0000
   9.500   1.2461   0.04424   0.04058  -0.0554   0.0017   1.0000
   9.750   1.2442   0.04761   0.04420  -0.0519   0.0017   1.0000
  10.000   1.2393   0.05072   0.04753  -0.0484   0.0018   1.0000
  10.250   1.2267   0.05359   0.05057  -0.0440   0.0018   1.0000
  10.500   1.2114   0.05621   0.05335  -0.0398   0.0018   1.0000
  10.750   1.1940   0.05924   0.05654  -0.0366   0.0018   1.0000
  11.000   1.1765   0.06265   0.06011  -0.0345   0.0018   1.0000
  11.250   1.1583   0.06657   0.06416  -0.0336   0.0019   1.0000
  11.500   1.1392   0.07111   0.06884  -0.0338   0.0019   1.0000
  11.750   1.1217   0.07595   0.07381  -0.0350   0.0019   1.0000
  12.000   1.1020   0.08177   0.07976  -0.0374   0.0019   1.0000
  12.250   1.0810   0.08873   0.08685  -0.0411   0.0019   1.0000
  12.500   1.0647   0.09549   0.09371  -0.0453   0.0019   1.0000
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