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GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 517 AIRFOIL (goe517-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.71 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe517-il-1000000.txt
Download as CSV file: xf-goe517-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 517 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2806   0.08537   0.08386  -0.0274   1.0000   0.0107
  -8.750  -0.2783   0.08235   0.08085  -0.0277   1.0000   0.0111
  -8.500  -0.2772   0.07912   0.07763  -0.0281   1.0000   0.0116
  -8.250  -0.2775   0.07581   0.07434  -0.0283   1.0000   0.0119
  -8.000  -0.2798   0.07234   0.07090  -0.0287   1.0000   0.0126
  -7.750  -0.3630   0.08344   0.08193  -0.0246   1.0000   0.0111
  -7.500  -0.3715   0.08149   0.08001  -0.0232   1.0000   0.0113
  -7.250  -0.3647   0.07788   0.07643  -0.0264   0.9988   0.0117
  -7.000  -0.3356   0.07142   0.06993  -0.0379   0.9932   0.0129
  -6.750  -0.3068   0.06594   0.06441  -0.0465   0.9867   0.0132
  -6.500  -0.2793   0.06024   0.05866  -0.0541   0.9798   0.0132
  -6.250  -0.2483   0.05451   0.05285  -0.0617   0.9724   0.0132
  -5.750  -0.2187   0.01628   0.01274  -0.0790   0.9309   0.0113
  -5.500  -0.1951   0.01440   0.01048  -0.0784   0.9156   0.0116
  -5.250  -0.1713   0.01303   0.00877  -0.0776   0.9012   0.0121
  -5.000  -0.1466   0.01212   0.00762  -0.0769   0.8881   0.0126
  -4.750  -0.1202   0.01188   0.00725  -0.0764   0.8767   0.0131
  -4.500  -0.0973   0.01032   0.00537  -0.0755   0.8662   0.0141
  -4.250  -0.0715   0.00995   0.00492  -0.0750   0.8565   0.0150
  -4.000  -0.0455   0.00957   0.00443  -0.0744   0.8467   0.0157
  -3.750  -0.0196   0.00920   0.00395  -0.0739   0.8364   0.0166
  -3.500   0.0065   0.00896   0.00361  -0.0733   0.8263   0.0175
  -3.250   0.0319   0.00840   0.00294  -0.0726   0.8165   0.0189
  -3.000   0.0579   0.00812   0.00260  -0.0721   0.8075   0.0208
  -2.750   0.0842   0.00793   0.00234  -0.0716   0.7983   0.0225
  -2.500   0.1108   0.00778   0.00214  -0.0712   0.7882   0.0240
  -2.250   0.1365   0.00743   0.00173  -0.0706   0.7782   0.0279
  -2.000   0.1628   0.00732   0.00157  -0.0701   0.7676   0.0316
  -1.750   0.1889   0.00713   0.00136  -0.0696   0.7548   0.0398
  -1.500   0.2151   0.00702   0.00125  -0.0691   0.7407   0.0540
  -1.250   0.2415   0.00697   0.00118  -0.0687   0.7252   0.0673
  -1.000   0.2678   0.00693   0.00113  -0.0683   0.7075   0.0779
  -0.750   0.2939   0.00692   0.00106  -0.0678   0.6864   0.0856
  -0.500   0.3197   0.00697   0.00102  -0.0673   0.6606   0.0932
  -0.250   0.3450   0.00702   0.00097  -0.0666   0.6306   0.1016
   0.000   0.3706   0.00710   0.00096  -0.0661   0.6038   0.1100
   0.250   0.3963   0.00715   0.00095  -0.0656   0.5825   0.1230
   0.500   0.4221   0.00717   0.00095  -0.0651   0.5656   0.1401
   1.000   0.4731   0.00697   0.00102  -0.0642   0.5414   0.2796
   1.250   0.5278   0.00542   0.00122  -0.0707   0.5301   0.9868
   1.500   0.5837   0.00555   0.00125  -0.0770   0.5180   0.9993
   2.000   0.6375   0.00572   0.00132  -0.0766   0.5004   1.0000
   2.250   0.6622   0.00581   0.00138  -0.0759   0.4914   1.0000
   2.500   0.6870   0.00591   0.00143  -0.0752   0.4807   1.0000
   2.750   0.7119   0.00599   0.00148  -0.0745   0.4695   1.0000
   3.000   0.7367   0.00610   0.00154  -0.0738   0.4566   1.0000
   3.250   0.7607   0.00625   0.00162  -0.0730   0.4360   1.0000
   3.500   0.7843   0.00645   0.00170  -0.0722   0.4059   1.0000
   3.750   0.8072   0.00671   0.00183  -0.0712   0.3745   1.0000
   4.250   0.8535   0.00721   0.00214  -0.0694   0.3315   1.0000
   4.500   0.8770   0.00743   0.00231  -0.0685   0.3159   1.0000
   4.750   0.9004   0.00767   0.00248  -0.0677   0.2985   1.0000
   5.000   0.9241   0.00789   0.00264  -0.0669   0.2845   1.0000
   5.250   0.9478   0.00811   0.00282  -0.0661   0.2694   1.0000
   5.500   0.9717   0.00831   0.00299  -0.0654   0.2570   1.0000
   5.750   0.9952   0.00856   0.00318  -0.0646   0.2406   1.0000
   6.000   1.0180   0.00885   0.00339  -0.0637   0.2215   1.0000
   6.250   1.0410   0.00913   0.00362  -0.0628   0.2018   1.0000
   6.500   1.0620   0.00960   0.00393  -0.0617   0.1691   1.0000
   6.750   1.0758   0.01069   0.00458  -0.0595   0.0926   1.0000
   7.000   1.0930   0.01151   0.00518  -0.0577   0.0545   1.0000
   7.250   1.1117   0.01221   0.00572  -0.0562   0.0290   1.0000
   7.500   1.1324   0.01271   0.00622  -0.0550   0.0219   1.0000
   7.750   1.1533   0.01319   0.00670  -0.0538   0.0186   1.0000
   8.000   1.1737   0.01372   0.00729  -0.0525   0.0162   1.0000
   8.250   1.1951   0.01412   0.00773  -0.0515   0.0150   1.0000
   8.500   1.2156   0.01460   0.00824  -0.0503   0.0137   1.0000
   8.750   1.2329   0.01535   0.00907  -0.0486   0.0123   1.0000
   9.000   1.2499   0.01608   0.00990  -0.0469   0.0116   1.0000
   9.250   1.2696   0.01656   0.01043  -0.0457   0.0110   1.0000
   9.500   1.2887   0.01705   0.01096  -0.0444   0.0104   1.0000
   9.750   1.3065   0.01762   0.01158  -0.0429   0.0097   1.0000
  10.000   1.3226   0.01827   0.01229  -0.0412   0.0092   1.0000
  10.250   1.3322   0.01934   0.01344  -0.0384   0.0087   1.0000
  10.500   1.3315   0.02077   0.01501  -0.0340   0.0082   1.0000
  10.750   1.3428   0.02141   0.01572  -0.0315   0.0080   1.0000
  11.000   1.3509   0.02227   0.01667  -0.0287   0.0079   1.0000
  11.250   1.3600   0.02312   0.01759  -0.0263   0.0076   1.0000
  11.500   1.3665   0.02419   0.01875  -0.0237   0.0074   1.0000
  11.750   1.3712   0.02545   0.02010  -0.0211   0.0073   1.0000
  12.000   1.3775   0.02666   0.02140  -0.0190   0.0070   1.0000
  12.250   1.3835   0.02798   0.02282  -0.0172   0.0068   1.0000
  12.500   1.3845   0.02980   0.02475  -0.0151   0.0067   1.0000
  12.750   1.3934   0.03102   0.02602  -0.0140   0.0065   1.0000
  13.000   1.3979   0.03270   0.02777  -0.0128   0.0063   1.0000
  13.250   1.3997   0.03472   0.02987  -0.0118   0.0060   1.0000
  13.500   1.3948   0.03756   0.03283  -0.0106   0.0059   1.0000
  13.750   1.3793   0.04171   0.03716  -0.0094   0.0057   1.0000
  14.000   1.3746   0.04488   0.04046  -0.0089   0.0057   1.0000
  14.250   1.3663   0.04867   0.04441  -0.0088   0.0056   1.0000
  14.500   1.3620   0.05211   0.04798  -0.0090   0.0055   1.0000
  14.750   1.3613   0.05527   0.05126  -0.0097   0.0055   1.0000
  15.000   1.3610   0.05852   0.05463  -0.0107   0.0053   1.0000
  15.250   1.3527   0.06296   0.05922  -0.0119   0.0053   1.0000
  15.500   1.3446   0.06750   0.06388  -0.0133   0.0052   1.0000
  15.750   1.3388   0.07193   0.06844  -0.0150   0.0051   1.0000
  16.000   1.3238   0.07778   0.07444  -0.0169   0.0051   1.0000
  16.250   1.3114   0.08348   0.08029  -0.0192   0.0051   1.0000
  16.500   1.3030   0.08886   0.08578  -0.0217   0.0050   1.0000
  16.750   1.2890   0.09527   0.09233  -0.0247   0.0050   1.0000
  17.000   1.2720   0.10250   0.09971  -0.0281   0.0050   1.0000
  17.250   1.2565   0.10979   0.10714  -0.0318   0.0050   1.0000
  17.500   1.2377   0.11793   0.11544  -0.0360   0.0050   1.0000
  17.750   1.2216   0.12581   0.12344  -0.0403   0.0051   1.0000
  18.000   1.2075   0.13353   0.13127  -0.0447   0.0050   1.0000
  18.250   1.1905   0.14211   0.13998  -0.0496   0.0050   1.0000
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