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GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)
Reynolds number: 200,000
Max Cl/Cd: 73.73 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe321-il-200000-n5.txt
Download as CSV file: xf-goe321-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2771   0.09016   0.08609  -0.0247   0.7544   0.0372
  -7.750  -0.2704   0.08710   0.08300  -0.0267   0.7467   0.0380
  -7.500  -0.2655   0.08393   0.07981  -0.0300   0.7395   0.0396
  -7.250  -0.2544   0.07800   0.07375  -0.0452   0.7328   0.0410
  -7.000  -0.2390   0.07340   0.06900  -0.0511   0.7270   0.0411
  -6.750  -0.2278   0.06996   0.06558  -0.0507   0.7202   0.0414
  -6.500  -0.2144   0.06727   0.06284  -0.0505   0.7138   0.0418
  -6.250  -0.1988   0.06451   0.06004  -0.0515   0.7075   0.0423
  -6.000  -0.1811   0.06157   0.05702  -0.0535   0.7006   0.0430
  -5.750  -0.1618   0.05855   0.05389  -0.0559   0.6947   0.0440
  -5.500  -0.1263   0.05361   0.04846  -0.0641   0.6883   0.0482
  -5.250  -0.1033   0.05006   0.04465  -0.0660   0.6820   0.0482
  -5.000  -0.0807   0.04683   0.04119  -0.0672   0.6764   0.0483
  -4.750  -0.0621   0.04128   0.03557  -0.0682   0.6702   0.0414
  -4.500  -0.0408   0.03974   0.03401  -0.0683   0.6641   0.0399
  -4.250  -0.0154   0.03693   0.03097  -0.0692   0.6582   0.0397
  -4.000   0.0111   0.03409   0.02786  -0.0700   0.6519   0.0398
  -3.750   0.0371   0.03167   0.02518  -0.0705   0.6467   0.0391
  -3.500   0.0642   0.02917   0.02240  -0.0709   0.6405   0.0384
  -3.250   0.0918   0.02683   0.01973  -0.0711   0.6345   0.0380
  -3.000   0.1196   0.02477   0.01731  -0.0712   0.6294   0.0379
  -2.750   0.1479   0.02302   0.01526  -0.0713   0.6233   0.0381
  -2.500   0.1763   0.02164   0.01358  -0.0712   0.6182   0.0393
  -2.250   0.2046   0.02035   0.01197  -0.0712   0.6139   0.0397
  -2.000   0.2333   0.01922   0.01061  -0.0712   0.6087   0.0399
  -1.750   0.2619   0.01828   0.00944  -0.0711   0.6037   0.0402
  -1.500   0.2902   0.01752   0.00844  -0.0709   0.5990   0.0407
  -1.250   0.3187   0.01688   0.00767  -0.0709   0.5930   0.0411
  -1.000   0.3467   0.01628   0.00702  -0.0708   0.5869   0.0418
  -0.750   0.3745   0.01596   0.00665  -0.0708   0.5805   0.0432
  -0.500   0.4026   0.01564   0.00629  -0.0707   0.5722   0.0448
  -0.250   0.4303   0.01529   0.00584  -0.0705   0.5647   0.0461
   0.000   0.4582   0.01494   0.00546  -0.0704   0.5567   0.0471
   0.250   0.4860   0.01469   0.00512  -0.0702   0.5507   0.0482
   0.500   0.5139   0.01440   0.00489  -0.0703   0.5456   0.0499
   0.750   0.5420   0.01424   0.00476  -0.0703   0.5401   0.0522
   1.000   0.5699   0.01416   0.00462  -0.0702   0.5346   0.0561
   1.250   0.5979   0.01403   0.00452  -0.0702   0.5284   0.0605
   1.500   0.6260   0.01396   0.00442  -0.0702   0.5215   0.0663
   1.750   0.6538   0.01390   0.00432  -0.0701   0.5156   0.0772
   2.000   0.6818   0.01377   0.00432  -0.0702   0.5080   0.1052
   2.500   0.7369   0.01189   0.00442  -0.0700   0.4928   1.0000
   2.750   0.7644   0.01202   0.00446  -0.0699   0.4855   1.0000
   3.000   0.7919   0.01216   0.00453  -0.0698   0.4786   1.0000
   3.250   0.8194   0.01228   0.00462  -0.0697   0.4705   1.0000
   3.500   0.8467   0.01243   0.00471  -0.0696   0.4622   1.0000
   3.750   0.8739   0.01256   0.00481  -0.0695   0.4522   1.0000
   4.000   0.9011   0.01271   0.00493  -0.0694   0.4409   1.0000
   4.250   0.9280   0.01287   0.00505  -0.0693   0.4275   1.0000
   4.500   0.9545   0.01305   0.00518  -0.0691   0.4103   1.0000
   4.750   0.9801   0.01330   0.00530  -0.0689   0.3885   1.0000
   5.000   1.0049   0.01363   0.00550  -0.0685   0.3640   1.0000
   5.500   1.0524   0.01454   0.00612  -0.0676   0.3221   1.0000
   5.750   1.0759   0.01501   0.00650  -0.0671   0.3054   1.0000
   6.000   1.0993   0.01549   0.00690  -0.0666   0.2908   1.0000
   6.250   1.1224   0.01598   0.00733  -0.0661   0.2770   1.0000
   6.500   1.1457   0.01644   0.00776  -0.0657   0.2637   1.0000
   6.750   1.1686   0.01693   0.00820  -0.0651   0.2518   1.0000
   7.000   1.1909   0.01743   0.00868  -0.0646   0.2414   1.0000
   7.250   1.2125   0.01797   0.00918  -0.0639   0.2324   1.0000
   7.500   1.2345   0.01847   0.00968  -0.0633   0.2250   1.0000
   7.750   1.2553   0.01903   0.01023  -0.0625   0.2189   1.0000
   8.000   1.2761   0.01957   0.01078  -0.0617   0.2142   1.0000
   8.250   1.2968   0.02011   0.01136  -0.0610   0.2100   1.0000
   8.500   1.3164   0.02070   0.01196  -0.0600   0.2064   1.0000
   8.750   1.3347   0.02134   0.01262  -0.0590   0.2035   1.0000
   9.000   1.3530   0.02197   0.01328  -0.0579   0.2011   1.0000
   9.250   1.3716   0.02256   0.01395  -0.0569   0.1989   1.0000
   9.500   1.3892   0.02319   0.01464  -0.0558   0.1968   1.0000
   9.750   1.4042   0.02385   0.01537  -0.0543   0.1946   1.0000
  10.000   1.4185   0.02459   0.01616  -0.0528   0.1925   1.0000
  10.250   1.4322   0.02542   0.01703  -0.0513   0.1905   1.0000
  10.500   1.4448   0.02636   0.01798  -0.0499   0.1881   1.0000
  10.750   1.4593   0.02720   0.01891  -0.0488   0.1855   1.0000
  11.000   1.4734   0.02807   0.01991  -0.0478   0.1825   1.0000
  11.250   1.4863   0.02905   0.02099  -0.0467   0.1795   1.0000
  11.500   1.4981   0.03017   0.02217  -0.0457   0.1766   1.0000
  11.750   1.5085   0.03143   0.02344  -0.0447   0.1737   1.0000
  12.000   1.5205   0.03261   0.02471  -0.0439   0.1712   1.0000
  12.250   1.5323   0.03384   0.02610  -0.0433   0.1681   1.0000
  12.500   1.5419   0.03526   0.02766  -0.0427   0.1641   1.0000
  12.750   1.5491   0.03692   0.02937  -0.0421   0.1601   1.0000
  13.000   1.5558   0.03866   0.03113  -0.0415   0.1565   1.0000
  13.250   1.5644   0.04032   0.03301  -0.0412   0.1520   1.0000
  13.500   1.5693   0.04235   0.03515  -0.0410   0.1463   1.0000
  13.750   1.5718   0.04464   0.03751  -0.0407   0.1408   1.0000
  14.000   1.5778   0.04668   0.03972  -0.0407   0.1334   1.0000
  14.250   1.5807   0.04905   0.04219  -0.0406   0.1266   1.0000
  14.500   1.5833   0.05152   0.04476  -0.0405   0.1151   1.0000
  14.750   1.5746   0.05531   0.04849  -0.0408   0.0926   1.0000
  15.000   1.5553   0.06050   0.05354  -0.0412   0.0757   1.0000
  15.250   1.5380   0.06563   0.05864  -0.0417   0.0622   1.0000
  15.500   1.5205   0.07102   0.06404  -0.0425   0.0508   1.0000
  15.750   1.5029   0.07664   0.06970  -0.0435   0.0423   1.0000
  16.000   1.4860   0.08232   0.07546  -0.0448   0.0366   1.0000
  16.250   1.4694   0.08818   0.08141  -0.0462   0.0328   1.0000
  16.500   1.4529   0.09419   0.08756  -0.0479   0.0304   1.0000
  16.750   1.4354   0.10055   0.09405  -0.0499   0.0287   1.0000
  17.000   1.4188   0.10699   0.10063  -0.0521   0.0274   1.0000
  17.250   1.4009   0.11382   0.10761  -0.0547   0.0265   1.0000
  17.500   1.3819   0.12102   0.11497  -0.0576   0.0259   1.0000
  17.750   1.3624   0.12851   0.12262  -0.0608   0.0254   1.0000
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