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GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 584 AIRFOIL (goe584-il)
Reynolds number: 100,000
Max Cl/Cd: 55.04 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe584-il-100000-n5.txt
Download as CSV file: xf-goe584-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 584 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2860   0.10659   0.10152  -0.0483   1.0000   0.0519
 -10.250  -0.2926   0.10331   0.09832  -0.0487   1.0000   0.0521
 -10.000  -0.3075   0.10007   0.09520  -0.0489   1.0000   0.0527
  -9.750  -0.2908   0.09805   0.09321  -0.0495   0.9936   0.0550
  -9.500  -0.2723   0.09466   0.08980  -0.0531   0.9842   0.0569
  -9.250  -0.2613   0.08979   0.08492  -0.0583   0.9731   0.0573
  -9.000  -0.2490   0.08506   0.08017  -0.0639   0.9626   0.0588
  -8.750  -0.2397   0.07948   0.07456  -0.0711   0.9507   0.0605
  -8.500  -0.2346   0.07325   0.06830  -0.0790   0.9363   0.0612
  -8.250  -0.2372   0.06526   0.06022  -0.0894   0.9189   0.0621
  -7.750  -0.2420   0.04929   0.04364  -0.1033   0.8914   0.0648
  -7.500  -0.2232   0.04818   0.04249  -0.1032   0.8809   0.0661
  -7.250  -0.2040   0.04595   0.04010  -0.1044   0.8729   0.0681
  -7.000  -0.1945   0.04245   0.03628  -0.1051   0.8618   0.0699
  -6.750  -0.1829   0.03854   0.03193  -0.1057   0.8529   0.0712
  -6.500  -0.1693   0.03539   0.02827  -0.1055   0.8437   0.0735
  -6.250  -0.1525   0.03277   0.02507  -0.1051   0.8358   0.0751
  -6.000  -0.1333   0.03080   0.02261  -0.1044   0.8275   0.0760
  -5.750  -0.1107   0.02906   0.02062  -0.1042   0.8210   0.0774
  -5.500  -0.0889   0.02806   0.01952  -0.1035   0.8126   0.0791
  -5.250  -0.0633   0.02701   0.01825  -0.1034   0.8065   0.0807
  -5.000  -0.0409   0.02599   0.01701  -0.1026   0.7984   0.0818
  -4.750  -0.0157   0.02498   0.01575  -0.1021   0.7917   0.0830
  -4.500   0.0097   0.02409   0.01464  -0.1017   0.7854   0.0843
  -4.250   0.0341   0.02340   0.01376  -0.1010   0.7779   0.0863
  -4.000   0.0614   0.02271   0.01282  -0.1008   0.7723   0.0884
  -3.750   0.0859   0.02215   0.01210  -0.1001   0.7648   0.0898
  -3.500   0.1121   0.02149   0.01132  -0.0996   0.7584   0.0909
  -3.250   0.1389   0.02085   0.01064  -0.0994   0.7531   0.0925
  -3.000   0.1628   0.02044   0.01023  -0.0986   0.7455   0.0942
  -2.750   0.1896   0.02001   0.00975  -0.0982   0.7399   0.0964
  -2.500   0.2149   0.01971   0.00941  -0.0977   0.7337   0.0997
  -2.250   0.2399   0.01944   0.00909  -0.0970   0.7271   0.1033
  -2.000   0.2668   0.01908   0.00868  -0.0966   0.7220   0.1068
  -1.750   0.2905   0.01885   0.00850  -0.0959   0.7152   0.1106
  -1.500   0.3159   0.01864   0.00826  -0.0952   0.7091   0.1157
  -1.250   0.3433   0.01836   0.00795  -0.0949   0.7044   0.1230
  -1.000   0.3664   0.01825   0.00790  -0.0940   0.6972   0.1349
  -0.750   0.3922   0.01800   0.00778  -0.0935   0.6914   0.1610
  -0.500   0.4196   0.01771   0.00763  -0.0933   0.6867   0.2146
  -0.250   0.4430   0.01750   0.00772  -0.0927   0.6794   0.2858
   0.000   0.4690   0.01711   0.00765  -0.0924   0.6739   0.3983
   0.250   0.4895   0.01614   0.00775  -0.0904   0.6687   0.7118
   0.500   0.5759   0.01583   0.00771  -0.1018   0.6612   1.0000
   0.750   0.6011   0.01591   0.00762  -0.1010   0.6556   1.0000
   1.000   0.6230   0.01610   0.00772  -0.0999   0.6485   1.0000
   1.250   0.6465   0.01624   0.00775  -0.0989   0.6417   1.0000
   1.500   0.6721   0.01634   0.00771  -0.0983   0.6362   1.0000
   1.750   0.6930   0.01657   0.00791  -0.0970   0.6284   1.0000
   2.000   0.7184   0.01668   0.00792  -0.0963   0.6226   1.0000
   2.250   0.7410   0.01690   0.00809  -0.0953   0.6157   1.0000
   2.500   0.7644   0.01707   0.00821  -0.0944   0.6088   1.0000
   2.750   0.7906   0.01718   0.00822  -0.0939   0.6032   1.0000
   3.000   0.8111   0.01746   0.00852  -0.0926   0.5951   1.0000
   3.250   0.8368   0.01758   0.00857  -0.0920   0.5889   1.0000
   3.500   0.8585   0.01784   0.00883  -0.0909   0.5813   1.0000
   3.750   0.8824   0.01801   0.00898  -0.0900   0.5741   1.0000
   4.000   0.9060   0.01821   0.00916  -0.0892   0.5671   1.0000
   4.250   0.9281   0.01845   0.00940  -0.0881   0.5590   1.0000
   4.500   0.9530   0.01860   0.00952  -0.0874   0.5521   1.0000
   4.750   0.9735   0.01888   0.00985  -0.0861   0.5432   1.0000
   5.000   0.9985   0.01904   0.00996  -0.0855   0.5362   1.0000
   5.250   1.0182   0.01934   0.01033  -0.0841   0.5268   1.0000
   5.500   1.0422   0.01952   0.01050  -0.0833   0.5191   1.0000
   5.750   1.0619   0.01982   0.01086  -0.0819   0.5094   1.0000
   6.000   1.0838   0.02006   0.01111  -0.0808   0.5006   1.0000
   6.250   1.1045   0.02032   0.01140  -0.0795   0.4909   1.0000
   6.500   1.1235   0.02063   0.01176  -0.0780   0.4803   1.0000
   6.750   1.1436   0.02086   0.01198  -0.0766   0.4691   1.0000
   7.000   1.1618   0.02111   0.01221  -0.0749   0.4562   1.0000
   7.250   1.1772   0.02146   0.01260  -0.0728   0.4422   1.0000
   7.500   1.1924   0.02184   0.01300  -0.0708   0.4286   1.0000
   7.750   1.2079   0.02225   0.01343  -0.0688   0.4164   1.0000
   8.000   1.2234   0.02267   0.01385  -0.0669   0.4048   1.0000
   8.250   1.2368   0.02313   0.01432  -0.0646   0.3930   1.0000
   8.500   1.2476   0.02367   0.01490  -0.0620   0.3811   1.0000
   8.750   1.2585   0.02425   0.01550  -0.0595   0.3695   1.0000
   9.000   1.2698   0.02487   0.01609  -0.0571   0.3584   1.0000
   9.250   1.2793   0.02559   0.01686  -0.0547   0.3468   1.0000
   9.500   1.2889   0.02637   0.01768  -0.0524   0.3358   1.0000
   9.750   1.2983   0.02720   0.01851  -0.0502   0.3250   1.0000
  10.000   1.3064   0.02814   0.01949  -0.0480   0.3138   1.0000
  10.250   1.3138   0.02917   0.02057  -0.0459   0.3027   1.0000
  10.500   1.3214   0.03024   0.02164  -0.0439   0.2923   1.0000
  10.750   1.3277   0.03144   0.02288  -0.0420   0.2815   1.0000
  11.000   1.3339   0.03272   0.02424  -0.0402   0.2711   1.0000
  11.250   1.3401   0.03404   0.02558  -0.0385   0.2615   1.0000
  11.500   1.3441   0.03555   0.02713  -0.0368   0.2508   1.0000
  11.750   1.3471   0.03719   0.02884  -0.0352   0.2400   1.0000
  12.000   1.3490   0.03898   0.03064  -0.0337   0.2292   1.0000
  12.250   1.3492   0.04094   0.03257  -0.0322   0.2186   1.0000
  12.500   1.3496   0.04302   0.03475  -0.0310   0.2077   1.0000
  12.750   1.3495   0.04521   0.03698  -0.0300   0.1976   1.0000
  13.000   1.3490   0.04748   0.03923  -0.0290   0.1891   1.0000
  13.250   1.3497   0.04982   0.04169  -0.0282   0.1800   1.0000
  13.500   1.3498   0.05219   0.04404  -0.0275   0.1733   1.0000
  13.750   1.3510   0.05464   0.04665  -0.0270   0.1656   1.0000
  14.000   1.3489   0.05742   0.04943  -0.0266   0.1585   1.0000
  14.250   1.3483   0.06021   0.05235  -0.0264   0.1511   1.0000
  14.500   1.3453   0.06333   0.05555  -0.0263   0.1440   1.0000
  14.750   1.3429   0.06646   0.05875  -0.0264   0.1377   1.0000
  15.000   1.3400   0.06982   0.06224  -0.0266   0.1308   1.0000
  15.250   1.3333   0.07366   0.06608  -0.0271   0.1244   1.0000
  15.500   1.3287   0.07750   0.07009  -0.0277   0.1169   1.0000
  15.750   1.3214   0.08171   0.07436  -0.0286   0.1106   1.0000
  16.000   1.3147   0.08603   0.07882  -0.0296   0.1035   1.0000
  16.250   1.3049   0.09088   0.08374  -0.0309   0.0967   1.0000
  16.500   1.2960   0.09580   0.08879  -0.0324   0.0887   1.0000
  16.750   1.2844   0.10125   0.09434  -0.0342   0.0803   1.0000
  17.000   1.2726   0.10687   0.10002  -0.0363   0.0719   1.0000
  17.250   1.2604   0.11264   0.10584  -0.0385   0.0640   1.0000
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