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GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 505 AIRFOIL (goe505-il)
Reynolds number: 200,000
Max Cl/Cd: 68.74 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe505-il-200000.txt
Download as CSV file: xf-goe505-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 505 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1439   0.09209   0.08870  -0.0897   0.9313   0.0808
  -8.000  -0.1652   0.08745   0.08401  -0.0994   0.9249   0.0815
  -7.750  -0.1851   0.08550   0.08214  -0.0921   0.9162   0.0819
  -7.500  -0.1631   0.08266   0.07931  -0.0902   0.9149   0.0829
  -7.250  -0.1418   0.08027   0.07691  -0.0903   0.9129   0.0843
  -7.000  -0.1200   0.07758   0.07420  -0.0924   0.9109   0.0870
  -6.750  -0.1413   0.07654   0.07319  -0.0877   0.9010   0.0880
  -6.500  -0.1530   0.06852   0.06486  -0.0988   0.8943   0.0949
  -5.750  -0.2370   0.04011   0.03478  -0.0861   0.8689   0.0596
  -5.500  -0.2165   0.03655   0.03081  -0.0859   0.8663   0.0592
  -5.250  -0.1872   0.03382   0.02755  -0.0865   0.8645   0.0596
  -5.000  -0.1897   0.03276   0.02626  -0.0811   0.8541   0.0595
  -4.750  -0.1554   0.03050   0.02360  -0.0821   0.8513   0.0596
  -4.500  -0.1127   0.02808   0.02082  -0.0844   0.8495   0.0602
  -4.250  -0.1030   0.02721   0.01982  -0.0809   0.8396   0.0607
  -4.000  -0.0570   0.02552   0.01802  -0.0837   0.8365   0.0623
  -3.750  -0.0077   0.02416   0.01657  -0.0870   0.8349   0.0651
  -3.500   0.0410   0.02280   0.01507  -0.0902   0.8339   0.0678
  -3.250   0.0436   0.02284   0.01504  -0.0854   0.8236   0.0690
  -3.000   0.0825   0.02171   0.01390  -0.0870   0.8217   0.0719
  -2.750   0.1247   0.02075   0.01296  -0.0892   0.8203   0.0774
  -2.500   0.1711   0.01968   0.01192  -0.0922   0.8191   0.0878
  -2.250   0.2194   0.01858   0.01101  -0.0958   0.8180   0.1267
  -2.000   0.2721   0.01799   0.01046  -0.1003   0.8168   0.1650
  -1.750   0.2685   0.01824   0.01072  -0.0938   0.8054   0.1740
  -1.500   0.3169   0.01776   0.01022  -0.0975   0.8033   0.1957
  -1.250   0.3672   0.01724   0.00963  -0.1015   0.8012   0.2184
  -1.000   0.3733   0.01724   0.00970  -0.0970   0.7908   0.2284
  -0.750   0.4187   0.01665   0.00911  -0.1000   0.7869   0.2487
  -0.500   0.4528   0.01627   0.00873  -0.1009   0.7811   0.2672
  -0.250   0.4730   0.01603   0.00853  -0.0990   0.7722   0.2816
   0.000   0.5198   0.01545   0.00793  -0.1025   0.7678   0.3005
   0.250   0.5265   0.01534   0.00788  -0.0979   0.7560   0.3101
   0.500   0.5523   0.01500   0.00755  -0.0971   0.7471   0.3245
   0.750   0.5790   0.01460   0.00717  -0.0965   0.7371   0.3410
   1.000   0.5903   0.01439   0.00700  -0.0927   0.7237   0.3566
   1.250   0.6031   0.01408   0.00676  -0.0893   0.7092   0.3765
   1.500   0.6185   0.01371   0.00645  -0.0864   0.6929   0.4038
   1.750   0.6331   0.01318   0.00609  -0.0833   0.6749   0.4543
   2.000   0.8909   0.01296   0.00647  -0.1310   0.6033   1.0000
   2.250   0.8966   0.01331   0.00652  -0.1264   0.5672   1.0000
   2.500   0.8993   0.01372   0.00666  -0.1213   0.5354   1.0000
   2.750   0.9020   0.01414   0.00684  -0.1163   0.5100   1.0000
   3.000   0.9050   0.01450   0.00702  -0.1114   0.4903   1.0000
   3.250   0.9101   0.01485   0.00720  -0.1070   0.4746   1.0000
   3.500   0.9185   0.01521   0.00741  -0.1032   0.4616   1.0000
   3.750   0.9291   0.01554   0.00761  -0.1000   0.4503   1.0000
   4.000   0.9414   0.01586   0.00784  -0.0970   0.4400   1.0000
   4.250   0.9564   0.01625   0.00805  -0.0947   0.4308   1.0000
   4.500   0.9677   0.01651   0.00830  -0.0916   0.4215   1.0000
   4.750   0.9860   0.01690   0.00854  -0.0899   0.4139   1.0000
   5.000   0.9996   0.01717   0.00881  -0.0873   0.4065   1.0000
   5.250   1.0186   0.01754   0.00906  -0.0859   0.3999   1.0000
   5.500   1.0371   0.01787   0.00937  -0.0843   0.3943   1.0000
   5.750   1.0549   0.01818   0.00967  -0.0826   0.3888   1.0000
   6.000   1.0776   0.01855   0.00995  -0.0818   0.3838   1.0000
   6.250   1.0980   0.01891   0.01031  -0.0807   0.3790   1.0000
   6.500   1.1149   0.01923   0.01065  -0.0788   0.3739   1.0000
   6.750   1.1352   0.01959   0.01097  -0.0777   0.3692   1.0000
   7.000   1.1616   0.02003   0.01133  -0.0777   0.3647   1.0000
   7.250   1.1755   0.02036   0.01175  -0.0754   0.3601   1.0000
   7.500   1.1939   0.02072   0.01212  -0.0739   0.3556   1.0000
   7.750   1.2178   0.02114   0.01248  -0.0736   0.3511   1.0000
   8.000   1.2361   0.02156   0.01295  -0.0721   0.3465   1.0000
   8.250   1.2477   0.02192   0.01337  -0.0695   0.3412   1.0000
   8.500   1.2630   0.02229   0.01368  -0.0676   0.3349   1.0000
   8.750   1.2743   0.02273   0.01417  -0.0651   0.3292   1.0000
   9.000   1.2841   0.02313   0.01462  -0.0623   0.3233   1.0000
   9.250   1.3025   0.02356   0.01499  -0.0611   0.3177   1.0000
   9.500   1.3095   0.02405   0.01559  -0.0580   0.3121   1.0000
   9.750   1.3181   0.02452   0.01611  -0.0553   0.3061   1.0000
  10.000   1.3343   0.02501   0.01653  -0.0538   0.3003   1.0000
  10.250   1.3396   0.02559   0.01728  -0.0508   0.2948   1.0000
  10.500   1.3490   0.02615   0.01790  -0.0484   0.2893   1.0000
  10.750   1.3624   0.02673   0.01845  -0.0467   0.2840   1.0000
  11.000   1.3644   0.02748   0.01937  -0.0436   0.2767   1.0000
  11.250   1.3718   0.02822   0.02008  -0.0412   0.2701   1.0000
  11.500   1.3770   0.02907   0.02109  -0.0388   0.2625   1.0000
  11.750   1.3828   0.02998   0.02201  -0.0366   0.2552   1.0000
  12.000   1.3909   0.03090   0.02305  -0.0347   0.2473   1.0000
  12.250   1.3947   0.03206   0.02421  -0.0325   0.2382   1.0000
  12.500   1.4010   0.03320   0.02543  -0.0307   0.2273   1.0000
  12.750   1.4060   0.03453   0.02680  -0.0289   0.2150   1.0000
  13.000   1.4091   0.03606   0.02832  -0.0271   0.2018   1.0000
  13.250   1.4078   0.03801   0.03021  -0.0251   0.1857   1.0000
  13.500   1.4062   0.04012   0.03226  -0.0232   0.1717   1.0000
  13.750   1.4031   0.04246   0.03457  -0.0215   0.1579   1.0000
  14.000   1.3971   0.04517   0.03723  -0.0197   0.1417   1.0000
  14.250   1.3883   0.04829   0.04028  -0.0182   0.1152   1.0000
  14.500   1.3619   0.05336   0.04513  -0.0164   0.0797   1.0000
  14.750   1.3318   0.05921   0.05088  -0.0152   0.0499   1.0000
  15.000   1.3128   0.06421   0.05590  -0.0148   0.0381   1.0000
  15.250   1.2985   0.06892   0.06068  -0.0147   0.0338   1.0000
  15.500   1.2890   0.07318   0.06506  -0.0149   0.0322   1.0000
  15.750   1.2784   0.07773   0.06976  -0.0153   0.0311   1.0000
  16.000   1.2666   0.08258   0.07476  -0.0160   0.0301   1.0000
  16.250   1.2542   0.08765   0.07998  -0.0169   0.0295   1.0000
  16.500   1.2393   0.09319   0.08567  -0.0181   0.0289   1.0000
  16.750   1.2227   0.09911   0.09174  -0.0195   0.0282   1.0000
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