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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 500,000
Max Cl/Cd: 100.58 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe673-il-500000.txt
Download as CSV file: xf-goe673-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 673 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4328   0.08400   0.08184  -0.0451   1.0000   0.0186
  -9.000  -0.4370   0.07885   0.07672  -0.0478   1.0000   0.0187
  -8.750  -0.4480   0.07354   0.07147  -0.0498   1.0000   0.0187
  -8.000  -0.4818   0.05603   0.05366  -0.0640   0.9929   0.0187
  -7.750  -0.4680   0.05049   0.04778  -0.0696   0.9877   0.0188
  -7.500  -0.4486   0.04555   0.04246  -0.0739   0.9847   0.0189
  -7.250  -0.4453   0.03501   0.03139  -0.0778   0.9798   0.0201
  -7.000  -0.4204   0.03199   0.02824  -0.0796   0.9765   0.0209
  -6.750  -0.3917   0.02934   0.02537  -0.0817   0.9742   0.0220
  -6.500  -0.3605   0.02679   0.02252  -0.0838   0.9724   0.0238
  -6.250  -0.3288   0.02133   0.01627  -0.0841   0.9706   0.0170
  -6.000  -0.3012   0.01865   0.01323  -0.0842   0.9667   0.0162
  -5.750  -0.2722   0.01720   0.01158  -0.0846   0.9625   0.0167
  -5.500  -0.2410   0.01612   0.01035  -0.0853   0.9594   0.0177
  -5.250  -0.2102   0.01465   0.00872  -0.0859   0.9566   0.0178
  -5.000  -0.1845   0.01373   0.00770  -0.0854   0.9509   0.0183
  -4.750  -0.1566   0.01306   0.00695  -0.0853   0.9460   0.0190
  -4.500  -0.1306   0.01159   0.00536  -0.0852   0.9419   0.0206
  -4.250  -0.1056   0.01106   0.00480  -0.0847   0.9349   0.0234
  -4.000  -0.0782   0.01059   0.00423  -0.0845   0.9297   0.0260
  -3.750  -0.0517   0.01019   0.00374  -0.0841   0.9234   0.0286
  -3.500  -0.0249   0.00969   0.00318  -0.0838   0.9171   0.0407
  -3.250  -0.0006   0.00845   0.00276  -0.0838   0.9107   0.2374
  -3.000   0.0256   0.00800   0.00257  -0.0837   0.9036   0.3281
  -2.750   0.0522   0.00763   0.00245  -0.0836   0.8971   0.4085
  -2.500   0.0790   0.00736   0.00235  -0.0835   0.8896   0.4748
  -2.250   0.1056   0.00706   0.00227  -0.0833   0.8825   0.5457
  -2.000   0.1322   0.00682   0.00219  -0.0831   0.8748   0.6051
  -1.750   0.1593   0.00668   0.00215  -0.0829   0.8668   0.6550
  -1.500   0.1865   0.00657   0.00209  -0.0826   0.8590   0.6938
  -1.250   0.2137   0.00649   0.00205  -0.0824   0.8497   0.7253
  -1.000   0.2408   0.00641   0.00199  -0.0821   0.8411   0.7536
  -0.750   0.2677   0.00632   0.00194  -0.0818   0.8316   0.7809
  -0.500   0.2940   0.00623   0.00191  -0.0814   0.8212   0.8118
  -0.250   0.3186   0.00612   0.00190  -0.0804   0.8108   0.8524
   0.000   0.3412   0.00604   0.00190  -0.0789   0.8000   0.9012
   0.250   0.3664   0.00601   0.00187  -0.0779   0.7886   0.9467
   0.500   0.4017   0.00600   0.00183  -0.0795   0.7761   0.9793
   0.750   0.4419   0.00601   0.00179  -0.0823   0.7629   1.0000
   1.000   0.4682   0.00607   0.00177  -0.0821   0.7487   1.0000
   1.250   0.4948   0.00615   0.00177  -0.0819   0.7340   1.0000
   1.500   0.5215   0.00625   0.00179  -0.0818   0.7185   1.0000
   1.750   0.5484   0.00635   0.00184  -0.0816   0.7018   1.0000
   2.000   0.5752   0.00647   0.00189  -0.0815   0.6849   1.0000
   2.250   0.6021   0.00660   0.00196  -0.0814   0.6689   1.0000
   2.500   0.6291   0.00674   0.00205  -0.0813   0.6536   1.0000
   2.750   0.6561   0.00688   0.00215  -0.0813   0.6388   1.0000
   3.000   0.6831   0.00704   0.00227  -0.0812   0.6244   1.0000
   3.250   0.7100   0.00719   0.00240  -0.0812   0.6100   1.0000
   3.500   0.7365   0.00738   0.00255  -0.0810   0.5924   1.0000
   3.750   0.7624   0.00758   0.00269  -0.0807   0.5669   1.0000
   4.000   0.7871   0.00786   0.00284  -0.0802   0.5314   1.0000
   4.250   0.8114   0.00819   0.00302  -0.0797   0.4928   1.0000
   4.500   0.8350   0.00860   0.00326  -0.0790   0.4450   1.0000
   4.750   0.8565   0.00922   0.00358  -0.0781   0.3790   1.0000
   5.000   0.8697   0.01071   0.00426  -0.0761   0.2248   1.0000
   5.250   0.8760   0.01311   0.00562  -0.0730   0.0304   1.0000
   5.500   0.8982   0.01381   0.00637  -0.0719   0.0236   1.0000
   5.750   0.9217   0.01430   0.00692  -0.0713   0.0207   1.0000
   6.000   0.9433   0.01498   0.00767  -0.0703   0.0185   1.0000
   6.250   0.9589   0.01623   0.00904  -0.0682   0.0168   1.0000
   6.500   0.9764   0.01722   0.01013  -0.0665   0.0161   1.0000
   6.750   0.9952   0.01807   0.01106  -0.0650   0.0154   1.0000
   7.000   1.0142   0.01888   0.01193  -0.0636   0.0144   1.0000
   7.250   1.0327   0.01972   0.01283  -0.0622   0.0134   1.0000
   7.500   1.0495   0.02081   0.01399  -0.0605   0.0129   1.0000
   7.750   1.0664   0.02199   0.01523  -0.0589   0.0123   1.0000
   8.000   1.0838   0.02340   0.01670  -0.0574   0.0119   1.0000
   8.250   1.1037   0.02543   0.01879  -0.0563   0.0115   1.0000
   8.500   1.1277   0.02779   0.02127  -0.0557   0.0114   1.0000
  19.000   0.6850   0.20740   0.20547  -0.0662   0.0109   1.0000
  19.250   0.6870   0.21093   0.20901  -0.0677   0.0109   1.0000
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