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GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 565 AIRFOIL (goe565-il)
Reynolds number: 200,000
Max Cl/Cd: 76.23 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe565-il-200000.txt
Download as CSV file: xf-goe565-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 565 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4301   0.08647   0.08288  -0.0318   1.0000   0.0550
  -8.250  -0.4339   0.08351   0.07998  -0.0322   1.0000   0.0570
  -8.000  -0.4461   0.08054   0.07709  -0.0327   1.0000   0.0589
  -7.750  -0.4604   0.07731   0.07395  -0.0337   1.0000   0.0597
  -7.250  -0.4905   0.06604   0.06248  -0.0452   1.0000   0.0617
  -7.000  -0.4992   0.05971   0.05611  -0.0453   1.0000   0.0626
  -6.750  -0.4864   0.06037   0.05700  -0.0395   1.0000   0.0647
  -6.500  -0.4818   0.05824   0.05486  -0.0381   1.0000   0.0667
  -6.250  -0.4776   0.05448   0.05100  -0.0389   1.0000   0.0702
  -6.000  -0.4766   0.04727   0.04328  -0.0426   1.0000   0.0763
  -5.750  -0.4658   0.03894   0.03434  -0.0430   1.0000   0.0602
  -5.500  -0.4534   0.03424   0.02934  -0.0426   1.0000   0.0578
  -5.250  -0.4369   0.02983   0.02438  -0.0421   1.0000   0.0571
  -5.000  -0.4175   0.02630   0.02030  -0.0413   1.0000   0.0573
  -4.750  -0.3927   0.02444   0.01791  -0.0410   0.9993   0.0606
  -4.500  -0.3594   0.02180   0.01476  -0.0426   0.9966   0.0635
  -4.250  -0.3244   0.02089   0.01380  -0.0446   0.9933   0.0681
  -4.000  -0.2895   0.01982   0.01245  -0.0460   0.9892   0.0714
  -3.750  -0.2515   0.01927   0.01158  -0.0480   0.9852   0.0746
  -3.500  -0.2149   0.01777   0.01002  -0.0500   0.9815   0.0778
  -3.250  -0.1782   0.01713   0.00933  -0.0518   0.9755   0.0813
  -3.000  -0.1372   0.01664   0.00876  -0.0544   0.9714   0.0858
  -2.750  -0.1035   0.01606   0.00811  -0.0555   0.9660   0.0885
  -2.500  -0.0691   0.01539   0.00753  -0.0570   0.9609   0.0932
  -2.250  -0.0292   0.01505   0.00717  -0.0594   0.9573   0.1007
  -2.000   0.0016   0.01454   0.00675  -0.0601   0.9510   0.1093
  -1.750   0.0372   0.01403   0.00631  -0.0617   0.9458   0.1258
  -1.500   0.0738   0.01282   0.00603  -0.0640   0.9425   0.3303
  -1.250   0.0999   0.01218   0.00605  -0.0638   0.9351   0.4968
  -1.000   0.1331   0.01156   0.00601  -0.0646   0.9300   0.6630
  -0.750   0.2160   0.01066   0.00581  -0.0749   0.9322   1.0000
  -0.500   0.2672   0.01039   0.00542  -0.0793   0.9282   1.0000
  -0.250   0.3002   0.01028   0.00523  -0.0801   0.9194   1.0000
   0.000   0.3422   0.01004   0.00492  -0.0826   0.9136   1.0000
   0.250   0.3727   0.00990   0.00472  -0.0826   0.9032   1.0000
   0.500   0.4082   0.00968   0.00446  -0.0836   0.8951   1.0000
   0.750   0.4376   0.00954   0.00427  -0.0834   0.8841   1.0000
   1.000   0.4641   0.00946   0.00416  -0.0826   0.8721   1.0000
   1.250   0.4912   0.00937   0.00404  -0.0820   0.8598   1.0000
   1.500   0.5181   0.00928   0.00393  -0.0812   0.8466   1.0000
   1.750   0.5446   0.00922   0.00384  -0.0804   0.8324   1.0000
   2.000   0.5705   0.00916   0.00375  -0.0795   0.8158   1.0000
   2.250   0.5966   0.00912   0.00367  -0.0785   0.7971   1.0000
   2.500   0.6223   0.00912   0.00362  -0.0776   0.7769   1.0000
   2.750   0.6475   0.00918   0.00364  -0.0766   0.7556   1.0000
   3.000   0.6729   0.00927   0.00367  -0.0756   0.7337   1.0000
   3.250   0.6973   0.00940   0.00376  -0.0745   0.7089   1.0000
   3.500   0.7209   0.00956   0.00384  -0.0733   0.6791   1.0000
   3.750   0.7432   0.00975   0.00392  -0.0717   0.6401   1.0000
   4.000   0.7640   0.01004   0.00399  -0.0699   0.5891   1.0000
   4.250   0.7836   0.01046   0.00415  -0.0680   0.5348   1.0000
   4.500   0.8036   0.01093   0.00440  -0.0663   0.4877   1.0000
   4.750   0.8239   0.01141   0.00469  -0.0648   0.4419   1.0000
   5.000   0.8435   0.01193   0.00501  -0.0632   0.3925   1.0000
   5.250   0.8632   0.01249   0.00539  -0.0617   0.3469   1.0000
   5.500   0.8826   0.01310   0.00579  -0.0602   0.3016   1.0000
   5.750   0.9026   0.01370   0.00622  -0.0589   0.2595   1.0000
   6.000   0.9232   0.01428   0.00666  -0.0576   0.2239   1.0000
   6.250   0.9427   0.01497   0.00719  -0.0563   0.1874   1.0000
   6.500   0.9604   0.01590   0.00786  -0.0547   0.1311   1.0000
   6.750   0.9748   0.01727   0.00878  -0.0526   0.0770   1.0000
   7.000   0.9924   0.01828   0.00976  -0.0509   0.0653   1.0000
   7.250   1.0091   0.01934   0.01080  -0.0490   0.0587   1.0000
   7.500   1.0275   0.02024   0.01180  -0.0474   0.0541   1.0000
   7.750   1.0451   0.02121   0.01278  -0.0458   0.0497   1.0000
   8.000   1.0594   0.02288   0.01443  -0.0437   0.0467   1.0000
   8.250   1.0790   0.02396   0.01564  -0.0423   0.0444   1.0000
   8.500   1.0982   0.02513   0.01688  -0.0410   0.0414   1.0000
   8.750   1.1174   0.02669   0.01844  -0.0399   0.0389   1.0000
   9.000   1.1410   0.02987   0.02172  -0.0395   0.0370   1.0000
   9.250   1.1606   0.03133   0.02342  -0.0381   0.0359   1.0000
   9.500   1.1785   0.03290   0.02524  -0.0367   0.0344   1.0000
   9.750   1.1949   0.03467   0.02723  -0.0351   0.0327   1.0000
  10.000   1.2104   0.03696   0.02977  -0.0336   0.0318   1.0000
  10.250   1.2236   0.03950   0.03257  -0.0318   0.0312   1.0000
  10.500   1.2329   0.04230   0.03566  -0.0297   0.0308   1.0000
  10.750   1.2367   0.04549   0.03921  -0.0271   0.0308   1.0000
  11.000   1.2389   0.04838   0.04234  -0.0245   0.0303   1.0000
  11.250   1.2371   0.05140   0.04558  -0.0219   0.0298   1.0000
  11.500   1.2283   0.05444   0.04885  -0.0184   0.0296   1.0000
  11.750   1.2150   0.05749   0.05215  -0.0149   0.0296   1.0000
  12.000   1.1999   0.06119   0.05605  -0.0124   0.0293   1.0000
  12.250   1.1818   0.06445   0.05956  -0.0102   0.0295   1.0000
  12.500   1.1005   0.07451   0.07041  -0.0108   0.0333   1.0000
  12.750   1.0706   0.08167   0.07778  -0.0140   0.0340   1.0000
  13.000   1.0416   0.08991   0.08617  -0.0188   0.0348   1.0000
  13.250   1.0146   0.09909   0.09547  -0.0248   0.0357   1.0000
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