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GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 362 AIRFOIL (goe362-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.44 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe362-il-1000000.txt
Download as CSV file: xf-goe362-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 362 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  -0.2507   0.08513   0.08363  -0.0268   1.0000   0.0098
  -8.500  -0.2491   0.08175   0.08026  -0.0272   1.0000   0.0099
  -8.250  -0.3245   0.09278   0.09118  -0.0230   1.0000   0.0098
  -8.000  -0.3218   0.09004   0.08847  -0.0236   1.0000   0.0098
  -7.750  -0.3236   0.08725   0.08571  -0.0236   1.0000   0.0099
  -7.500  -0.3280   0.08531   0.08381  -0.0221   1.0000   0.0098
  -5.500  -0.0993   0.01768   0.01476  -0.1017   0.9504   0.0103
  -5.250  -0.0733   0.01564   0.01240  -0.1021   0.9387   0.0107
  -5.000  -0.0477   0.01426   0.01074  -0.1019   0.9263   0.0112
  -4.750  -0.0223   0.01283   0.00900  -0.1016   0.9123   0.0116
  -4.500   0.0034   0.01157   0.00744  -0.1011   0.8968   0.0120
  -4.250   0.0293   0.01061   0.00622  -0.1005   0.8805   0.0124
  -4.000   0.0558   0.01014   0.00556  -0.1000   0.8636   0.0131
  -3.750   0.0817   0.00917   0.00431  -0.0994   0.8462   0.0140
  -3.500   0.1079   0.00870   0.00370  -0.0989   0.8289   0.0150
  -3.250   0.1346   0.00845   0.00334  -0.0984   0.8121   0.0159
  -2.750   0.1883   0.00805   0.00271  -0.0975   0.7787   0.0179
  -2.500   0.2150   0.00760   0.00214  -0.0971   0.7621   0.0204
  -2.250   0.2420   0.00753   0.00200  -0.0967   0.7448   0.0228
  -2.000   0.2689   0.00731   0.00167  -0.0962   0.7272   0.0255
  -1.750   0.2959   0.00720   0.00149  -0.0959   0.7099   0.0298
  -1.250   0.3499   0.00703   0.00118  -0.0951   0.6775   0.0413
  -1.000   0.3770   0.00694   0.00105  -0.0948   0.6626   0.0523
  -0.750   0.4041   0.00688   0.00102  -0.0945   0.6481   0.0797
  -0.500   0.4313   0.00690   0.00101  -0.0942   0.6341   0.0960
   0.000   0.4857   0.00691   0.00096  -0.0937   0.6057   0.1177
   0.500   0.5400   0.00691   0.00094  -0.0931   0.5747   0.1507
   0.750   0.5670   0.00688   0.00098  -0.0929   0.5563   0.2088
   1.250   0.6186   0.00646   0.00115  -0.0922   0.5117   0.5199
   1.500   0.6507   0.00561   0.00124  -0.0933   0.4874   1.0000
   1.750   0.6774   0.00578   0.00129  -0.0930   0.4671   1.0000
   2.000   0.7041   0.00595   0.00136  -0.0926   0.4511   1.0000
   2.250   0.7309   0.00610   0.00143  -0.0923   0.4381   1.0000
   2.500   0.7577   0.00624   0.00152  -0.0920   0.4271   1.0000
   2.750   0.7845   0.00639   0.00160  -0.0917   0.4174   1.0000
   3.000   0.8115   0.00651   0.00169  -0.0915   0.4079   1.0000
   3.250   0.8383   0.00666   0.00179  -0.0912   0.3974   1.0000
   3.500   0.8648   0.00683   0.00190  -0.0909   0.3864   1.0000
   3.750   0.8917   0.00696   0.00200  -0.0906   0.3750   1.0000
   4.000   0.9184   0.00710   0.00211  -0.0903   0.3643   1.0000
   4.250   0.9450   0.00725   0.00222  -0.0900   0.3529   1.0000
   4.500   0.9714   0.00742   0.00236  -0.0897   0.3416   1.0000
   4.750   0.9977   0.00760   0.00250  -0.0894   0.3276   1.0000
   5.000   1.0239   0.00779   0.00264  -0.0891   0.3131   1.0000
   5.250   1.0500   0.00800   0.00280  -0.0887   0.2989   1.0000
   5.500   1.0759   0.00822   0.00299  -0.0884   0.2831   1.0000
   5.750   1.1014   0.00848   0.00319  -0.0880   0.2648   1.0000
   6.000   1.1263   0.00881   0.00343  -0.0875   0.2439   1.0000
   6.250   1.1507   0.00920   0.00371  -0.0869   0.2175   1.0000
   6.500   1.1737   0.00975   0.00409  -0.0863   0.1805   1.0000
   6.750   1.1950   0.01052   0.00458  -0.0853   0.1330   1.0000
   7.000   1.2160   0.01132   0.00513  -0.0844   0.0914   1.0000
   7.250   1.2391   0.01184   0.00557  -0.0837   0.0752   1.0000
   7.500   1.2628   0.01225   0.00597  -0.0831   0.0656   1.0000
   7.750   1.2862   0.01270   0.00638  -0.0824   0.0571   1.0000
   8.000   1.3103   0.01304   0.00674  -0.0819   0.0522   1.0000
   8.250   1.3334   0.01348   0.00716  -0.0812   0.0455   1.0000
   8.500   1.3569   0.01387   0.00756  -0.0806   0.0404   1.0000
   8.750   1.3795   0.01433   0.00800  -0.0799   0.0334   1.0000
   9.000   1.3998   0.01504   0.00861  -0.0788   0.0213   1.0000
   9.250   1.4191   0.01583   0.00936  -0.0776   0.0145   1.0000
   9.500   1.4395   0.01646   0.01004  -0.0765   0.0125   1.0000
   9.750   1.4575   0.01734   0.01099  -0.0751   0.0105   1.0000
  10.000   1.4777   0.01791   0.01163  -0.0740   0.0099   1.0000
  10.250   1.4966   0.01857   0.01237  -0.0728   0.0092   1.0000
  10.500   1.5141   0.01932   0.01318  -0.0714   0.0086   1.0000
  10.750   1.5277   0.02037   0.01432  -0.0694   0.0079   1.0000
  11.000   1.5368   0.02169   0.01577  -0.0668   0.0074   1.0000
  11.250   1.5518   0.02242   0.01659  -0.0651   0.0071   1.0000
  11.500   1.5623   0.02325   0.01751  -0.0626   0.0069   1.0000
  11.750   1.5705   0.02410   0.01844  -0.0599   0.0066   1.0000
  12.000   1.5779   0.02502   0.01944  -0.0572   0.0063   1.0000
  12.250   1.5833   0.02613   0.02063  -0.0546   0.0061   1.0000
  12.500   1.5881   0.02735   0.02194  -0.0521   0.0058   1.0000
  12.750   1.5901   0.02888   0.02355  -0.0498   0.0056   1.0000
  13.000   1.5880   0.03087   0.02566  -0.0474   0.0055   1.0000
  13.250   1.5805   0.03355   0.02847  -0.0453   0.0053   1.0000
  13.500   1.5695   0.03688   0.03196  -0.0438   0.0051   1.0000
  13.750   1.5533   0.04117   0.03642  -0.0429   0.0050   1.0000
  14.000   1.5524   0.04404   0.03941  -0.0427   0.0050   1.0000
  14.250   1.5522   0.04699   0.04247  -0.0428   0.0049   1.0000
  14.500   1.5496   0.05040   0.04602  -0.0432   0.0048   1.0000
  14.750   1.5425   0.05455   0.05030  -0.0440   0.0048   1.0000
  15.000   1.5381   0.05851   0.05438  -0.0450   0.0047   1.0000
  15.250   1.5270   0.06360   0.05961  -0.0465   0.0047   1.0000
  15.500   1.5176   0.06865   0.06479  -0.0483   0.0046   1.0000
  15.750   1.5099   0.07369   0.06995  -0.0502   0.0046   1.0000
  16.000   1.4975   0.07965   0.07604  -0.0526   0.0045   1.0000
  16.250   1.4863   0.08561   0.08214  -0.0552   0.0045   1.0000
  16.500   1.4740   0.09196   0.08862  -0.0581   0.0045   1.0000
  16.750   1.4625   0.09829   0.09507  -0.0611   0.0044   1.0000
  17.000   1.4496   0.10505   0.10196  -0.0644   0.0044   1.0000
  17.250   1.4369   0.11197   0.10900  -0.0678   0.0044   1.0000
  17.500   1.4241   0.11903   0.11618  -0.0715   0.0043   1.0000
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