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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.79 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe100-il-1000000.txt
Download as CSV file: xf-goe100-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 100 (SOPWITH) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4050   0.08586   0.08440  -0.0195   1.0000   0.0076
  -7.250  -0.4072   0.08284   0.08141  -0.0202   1.0000   0.0076
  -7.000  -0.4111   0.08000   0.07860  -0.0202   1.0000   0.0076
  -6.750  -0.3919   0.07463   0.07321  -0.0269   0.9983   0.0076
  -6.500  -0.3647   0.06829   0.06683  -0.0356   0.9960   0.0076
  -6.250  -0.3412   0.05895   0.05741  -0.0465   0.9932   0.0084
  -6.000  -0.3141   0.05553   0.05393  -0.0511   0.9903   0.0089
  -5.750  -0.2836   0.05134   0.04966  -0.0564   0.9876   0.0096
  -5.500  -0.2497   0.04635   0.04456  -0.0622   0.9854   0.0106
  -5.250  -0.2105   0.04306   0.04116  -0.0662   0.9840   0.0128
  -4.750  -0.1513   0.01547   0.01181  -0.0749   0.9740   0.0083
  -4.500  -0.1189   0.01410   0.01016  -0.0758   0.9708   0.0079
  -4.250  -0.0904   0.01253   0.00830  -0.0758   0.9642   0.0078
  -4.000  -0.0619   0.00995   0.00525  -0.0758   0.9579   0.0084
  -3.750  -0.0341   0.00913   0.00431  -0.0757   0.9476   0.0097
  -3.500  -0.0064   0.00864   0.00370  -0.0754   0.9347   0.0106
  -3.250   0.0206   0.00820   0.00313  -0.0749   0.9214   0.0114
  -3.000   0.0478   0.00791   0.00276  -0.0746   0.9110   0.0125
  -2.750   0.0751   0.00752   0.00221  -0.0743   0.9021   0.0144
  -2.500   0.1025   0.00720   0.00182  -0.0739   0.8923   0.0190
  -2.250   0.1297   0.00701   0.00170  -0.0737   0.8817   0.0408
  -2.000   0.1570   0.00699   0.00164  -0.0735   0.8698   0.0488
  -1.750   0.1845   0.00696   0.00155  -0.0733   0.8594   0.0535
  -1.500   0.2122   0.00692   0.00148  -0.0732   0.8494   0.0556
  -1.250   0.2398   0.00684   0.00134  -0.0730   0.8387   0.0588
  -1.000   0.2674   0.00673   0.00123  -0.0729   0.8281   0.0654
  -0.750   0.2950   0.00668   0.00112  -0.0728   0.8150   0.0685
  -0.500   0.3223   0.00656   0.00103  -0.0726   0.7996   0.0899
  -0.250   0.3494   0.00645   0.00102  -0.0725   0.7813   0.1513
   0.000   0.3765   0.00645   0.00100  -0.0722   0.7566   0.1718
   0.250   0.4031   0.00650   0.00097  -0.0719   0.7243   0.1901
   0.500   0.4285   0.00662   0.00097  -0.0714   0.6676   0.2217
   0.750   0.4522   0.00672   0.00107  -0.0709   0.5866   0.3589
   1.000   0.4684   0.00561   0.00123  -0.0688   0.5310   0.8995
   1.250   0.4972   0.00573   0.00129  -0.0688   0.4849   0.9890
   1.500   0.5284   0.00600   0.00136  -0.0697   0.4412   1.0000
   1.750   0.5541   0.00626   0.00144  -0.0694   0.4006   1.0000
   2.000   0.5798   0.00653   0.00153  -0.0691   0.3642   1.0000
   2.250   0.6054   0.00685   0.00164  -0.0687   0.3233   1.0000
   2.500   0.6301   0.00727   0.00178  -0.0683   0.2682   1.0000
   2.750   0.6560   0.00755   0.00192  -0.0680   0.2352   1.0000
   3.000   0.6815   0.00789   0.00206  -0.0677   0.2003   1.0000
   3.250   0.7065   0.00830   0.00223  -0.0674   0.1590   1.0000
   3.750   0.7522   0.00983   0.00306  -0.0659   0.0160   1.0000
   4.000   0.7789   0.01003   0.00331  -0.0657   0.0136   1.0000
   4.250   0.8054   0.01027   0.00361  -0.0654   0.0124   1.0000
   4.500   0.8316   0.01054   0.00393  -0.0651   0.0114   1.0000
   4.750   0.8574   0.01089   0.00434  -0.0648   0.0105   1.0000
   5.000   0.8826   0.01134   0.00486  -0.0643   0.0094   1.0000
   5.250   0.9071   0.01193   0.00552  -0.0636   0.0085   1.0000
   5.500   0.9311   0.01258   0.00625  -0.0628   0.0084   1.0000
   5.750   0.9551   0.01324   0.00699  -0.0620   0.0088   1.0000
   6.000   0.9766   0.01416   0.00797  -0.0610   0.0080   1.0000
   6.250   0.9961   0.01536   0.00921  -0.0596   0.0077   1.0000
   6.500   1.0151   0.01664   0.01054  -0.0581   0.0076   1.0000
   6.750   1.0368   0.01756   0.01155  -0.0570   0.0066   1.0000
   7.000   1.0593   0.01841   0.01246  -0.0560   0.0062   1.0000
  11.000   1.1837   0.03990   0.03637  -0.0151   0.0045   1.0000
  11.250   1.1696   0.04267   0.03927  -0.0118   0.0044   1.0000
  11.500   1.1533   0.04580   0.04254  -0.0090   0.0044   1.0000
  11.750   1.1338   0.04946   0.04635  -0.0068   0.0044   1.0000
  12.000   1.1136   0.05364   0.05066  -0.0054   0.0044   1.0000
  12.250   1.0900   0.05854   0.05572  -0.0049   0.0044   1.0000
  12.500   1.0662   0.06400   0.06132  -0.0054   0.0044   1.0000
  12.750   1.0404   0.07020   0.06767  -0.0070   0.0044   1.0000
  13.000   1.0138   0.07715   0.07478  -0.0097   0.0045   1.0000
  13.250   0.9878   0.08439   0.08215  -0.0130   0.0045   1.0000
  13.500   0.9618   0.09211   0.09001  -0.0170   0.0046   1.0000
  13.750   0.9344   0.10025   0.09829  -0.0216   0.0047   1.0000
  14.000   0.9052   0.10867   0.10684  -0.0264   0.0049   1.0000
  14.250   0.8725   0.11564   0.11392  -0.0301   0.0052   1.0000
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