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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 100,000
Max Cl/Cd: 55.96 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe673-il-100000.txt
Download as CSV file: xf-goe673-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3228   0.09741   0.09290  -0.0379   1.0000   0.1233
  -9.250  -0.3379   0.09456   0.09014  -0.0392   1.0000   0.1285
  -9.000  -0.3753   0.09234   0.08808  -0.0422   1.0000   0.1299
  -8.750  -0.3377   0.08746   0.08313  -0.0375   1.0000   0.1347
  -8.500  -0.3436   0.08460   0.08034  -0.0367   1.0000   0.1398
  -8.250  -0.3835   0.08267   0.07857  -0.0379   1.0000   0.1432
  -8.000  -0.3778   0.07852   0.07446  -0.0355   1.0000   0.1461
  -7.750  -0.3727   0.07580   0.07176  -0.0328   1.0000   0.1502
  -7.500  -0.5144   0.08150   0.07727  -0.0414   1.0000   0.1443
  -7.250  -0.4842   0.07910   0.07494  -0.0332   1.0000   0.1487
  -5.500  -0.4742   0.03780   0.03063  -0.0448   1.0000   0.0637
  -5.250  -0.4531   0.03356   0.02623  -0.0448   1.0000   0.0601
  -5.000  -0.4287   0.03040   0.02254  -0.0445   1.0000   0.0570
  -4.750  -0.4035   0.02835   0.02006  -0.0442   1.0000   0.0583
  -4.500  -0.3774   0.02659   0.01792  -0.0438   1.0000   0.0597
  -4.250  -0.3507   0.02491   0.01592  -0.0434   1.0000   0.0599
  -4.000  -0.3246   0.02358   0.01441  -0.0430   1.0000   0.0613
  -3.750  -0.2991   0.02253   0.01325  -0.0426   1.0000   0.0638
  -3.500  -0.2736   0.02138   0.01222  -0.0427   1.0000   0.0726
  -3.250  -0.2472   0.02050   0.01132  -0.0429   1.0000   0.0822
  -3.000  -0.2176   0.01940   0.01054  -0.0437   1.0000   0.1285
  -2.750  -0.1863   0.01759   0.01055  -0.0454   1.0000   0.5052
  -2.500  -0.1641   0.01740   0.01097  -0.0442   0.9991   0.6500
  -2.250  -0.1326   0.01739   0.01132  -0.0436   0.9927   0.7852
  -2.000  -0.1039   0.01737   0.01143  -0.0425   0.9848   0.8873
  -1.750  -0.0523   0.01739   0.01118  -0.0479   0.9746   1.0000
  -1.500  -0.0044   0.01769   0.01112  -0.0531   0.9670   1.0000
  -1.250   0.0401   0.01793   0.01107  -0.0573   0.9582   1.0000
  -1.000   0.0802   0.01815   0.01108  -0.0605   0.9485   1.0000
  -0.750   0.1293   0.01836   0.01108  -0.0653   0.9420   1.0000
  -0.500   0.1650   0.01852   0.01108  -0.0674   0.9309   1.0000
  -0.250   0.2026   0.01868   0.01112  -0.0698   0.9208   1.0000
   0.000   0.2507   0.01871   0.01105  -0.0740   0.9144   1.0000
   0.250   0.2845   0.01882   0.01107  -0.0755   0.9031   1.0000
   0.500   0.3209   0.01889   0.01108  -0.0774   0.8929   1.0000
   0.750   0.3692   0.01873   0.01089  -0.0813   0.8869   1.0000
   1.000   0.4011   0.01876   0.01091  -0.0821   0.8755   1.0000
   1.250   0.4348   0.01874   0.01088  -0.0832   0.8651   1.0000
   1.500   0.4776   0.01844   0.01057  -0.0856   0.8586   1.0000
   1.750   0.5071   0.01842   0.01057  -0.0857   0.8467   1.0000
   2.000   0.5374   0.01836   0.01056  -0.0859   0.8352   1.0000
   2.250   0.5692   0.01822   0.01046  -0.0862   0.8245   1.0000
   2.500   0.6063   0.01784   0.01011  -0.0872   0.8164   1.0000
   2.750   0.6344   0.01776   0.01012  -0.0868   0.8036   1.0000
   3.000   0.6628   0.01767   0.01009  -0.0864   0.7907   1.0000
   3.250   0.6914   0.01756   0.01005  -0.0860   0.7775   1.0000
   3.500   0.7200   0.01746   0.01001  -0.0855   0.7639   1.0000
   3.750   0.7483   0.01737   0.01004  -0.0851   0.7499   1.0000
   4.000   0.7766   0.01732   0.01006  -0.0846   0.7354   1.0000
   4.250   0.8047   0.01731   0.01014  -0.0841   0.7206   1.0000
   4.500   0.8327   0.01733   0.01027  -0.0835   0.7055   1.0000
   4.750   0.8600   0.01744   0.01052  -0.0830   0.6897   1.0000
   5.000   0.8844   0.01708   0.01018  -0.0809   0.6604   1.0000
   5.250   0.9036   0.01654   0.00952  -0.0775   0.6115   1.0000
   5.500   0.9217   0.01647   0.00936  -0.0745   0.5608   1.0000
   5.750   0.9308   0.01676   0.00930  -0.0699   0.4610   1.0000
   6.000   0.9166   0.01975   0.01030  -0.0629   0.1535   1.0000
   6.250   0.9194   0.02245   0.01227  -0.0591   0.0787   1.0000
   6.500   0.9305   0.02406   0.01396  -0.0564   0.0673   1.0000
   6.750   0.9416   0.02553   0.01550  -0.0538   0.0599   1.0000
   7.000   0.9500   0.02733   0.01732  -0.0507   0.0568   1.0000
   7.250   0.9674   0.02887   0.01891  -0.0488   0.0544   1.0000
   7.500   0.9926   0.03071   0.02075  -0.0480   0.0520   1.0000
   7.750   1.0207   0.03284   0.02282  -0.0480   0.0479   1.0000
   8.000   1.0614   0.03654   0.02651  -0.0498   0.0462   1.0000
   8.250   1.0925   0.03925   0.02946  -0.0496   0.0465   1.0000
   8.500   1.1180   0.04145   0.03211  -0.0482   0.0482   1.0000
   8.750   1.1375   0.04490   0.03625  -0.0458   0.0522   1.0000
   9.000   1.1559   0.04913   0.04087  -0.0442   0.0550   1.0000
   9.250   1.1724   0.05450   0.04650  -0.0431   0.0568   1.0000
   9.500   1.2049   0.06179   0.05499  -0.0394   0.0965   1.0000
   9.750   1.1004   0.05152   0.04548  -0.0248   0.0774   1.0000
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