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GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il)
Reynolds number: 100,000
Max Cl/Cd: 54.36 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe323-il-100000-n5.txt
Download as CSV file: xf-goe323-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2998   0.10059   0.09515  -0.0100   0.7122   0.0580
  -8.000  -0.2956   0.09768   0.09225  -0.0137   0.7072   0.0596
  -7.750  -0.2960   0.09493   0.08951  -0.0208   0.7022   0.0604
  -7.500  -0.2875   0.09124   0.08574  -0.0305   0.6978   0.0607
  -7.250  -0.2762   0.08746   0.08197  -0.0254   0.6935   0.0615
  -7.000  -0.2631   0.08453   0.07906  -0.0239   0.6887   0.0629
  -6.750  -0.2504   0.08159   0.07610  -0.0257   0.6843   0.0648
  -6.500  -0.2367   0.07837   0.07283  -0.0295   0.6806   0.0672
  -6.250  -0.2129   0.07455   0.06868  -0.0439   0.6773   0.0705
  -6.000  -0.1978   0.07040   0.06454  -0.0452   0.6730   0.0712
  -5.750  -0.1838   0.06723   0.06141  -0.0442   0.6686   0.0721
  -5.500  -0.1672   0.06448   0.05862  -0.0446   0.6648   0.0735
  -5.250  -0.1482   0.06175   0.05578  -0.0462   0.6616   0.0756
  -4.750  -0.0996   0.05543   0.04913  -0.0535   0.6538   0.0843
  -4.500  -0.0803   0.05313   0.04683  -0.0536   0.6503   0.0870
  -4.250  -0.0531   0.05107   0.04450  -0.0560   0.6471   0.0939
  -4.000  -0.0281   0.04807   0.04124  -0.0581   0.6440   0.0979
  -3.750  -0.0061   0.04572   0.03890  -0.0586   0.6397   0.1000
  -3.500   0.0322   0.03967   0.03203  -0.0609   0.6365   0.0598
  -3.250   0.0572   0.03754   0.02975  -0.0613   0.6333   0.0586
  -3.000   0.0841   0.03548   0.02739  -0.0617   0.6304   0.0586
  -2.750   0.1110   0.03360   0.02522  -0.0619   0.6275   0.0581
  -2.500   0.1386   0.03175   0.02314  -0.0622   0.6233   0.0566
  -2.250   0.1667   0.03000   0.02106  -0.0623   0.6195   0.0553
  -2.000   0.1949   0.02847   0.01917  -0.0622   0.6162   0.0545
  -1.750   0.2229   0.02722   0.01758  -0.0619   0.6132   0.0542
  -1.500   0.2508   0.02623   0.01637  -0.0618   0.6096   0.0545
  -1.250   0.2784   0.02551   0.01554  -0.0618   0.6045   0.0561
  -1.000   0.3062   0.02474   0.01456  -0.0615   0.5996   0.0576
  -0.750   0.3340   0.02393   0.01351  -0.0610   0.5954   0.0582
  -0.500   0.3618   0.02329   0.01277  -0.0608   0.5895   0.0587
  -0.250   0.3895   0.02270   0.01208  -0.0605   0.5843   0.0594
   0.000   0.4172   0.02217   0.01142  -0.0600   0.5803   0.0602
   0.250   0.4443   0.02163   0.01087  -0.0597   0.5764   0.0620
   0.500   0.4710   0.02132   0.01067  -0.0596   0.5705   0.0650
   0.750   0.4978   0.02098   0.01032  -0.0592   0.5657   0.0677
   1.000   0.5247   0.02062   0.00989  -0.0586   0.5618   0.0697
   1.250   0.5512   0.02041   0.00972  -0.0583   0.5562   0.0722
   1.500   0.5781   0.02024   0.00957  -0.0580   0.5504   0.0769
   1.750   0.6055   0.02004   0.00930  -0.0576   0.5458   0.0844
   2.000   0.6330   0.01995   0.00920  -0.0574   0.5402   0.0942
   2.250   0.6602   0.01976   0.00921  -0.0573   0.5336   0.1341
   2.750   0.7211   0.01792   0.00911  -0.0578   0.5213   1.0000
   3.000   0.7477   0.01802   0.00909  -0.0574   0.5145   1.0000
   3.250   0.7745   0.01806   0.00900  -0.0570   0.5086   1.0000
   3.500   0.8004   0.01825   0.00919  -0.0567   0.4998   1.0000
   3.750   0.8275   0.01824   0.00903  -0.0562   0.4937   1.0000
   4.000   0.8530   0.01847   0.00931  -0.0560   0.4837   1.0000
   4.250   0.8796   0.01849   0.00922  -0.0555   0.4766   1.0000
   4.500   0.9052   0.01870   0.00947  -0.0552   0.4661   1.0000
   4.750   0.9311   0.01883   0.00958  -0.0548   0.4566   1.0000
   5.000   0.9569   0.01894   0.00966  -0.0544   0.4470   1.0000
   5.250   0.9822   0.01918   0.00993  -0.0541   0.4355   1.0000
   5.500   1.0075   0.01937   0.01010  -0.0537   0.4247   1.0000
   5.750   1.0329   0.01953   0.01020  -0.0532   0.4144   1.0000
   6.000   1.0574   0.01982   0.01051  -0.0528   0.4021   1.0000
   6.250   1.0818   0.02012   0.01078  -0.0524   0.3902   1.0000
   6.500   1.1058   0.02044   0.01105  -0.0519   0.3790   1.0000
   6.750   1.1295   0.02078   0.01131  -0.0513   0.3686   1.0000
   7.000   1.1526   0.02125   0.01180  -0.0508   0.3580   1.0000
   7.250   1.1755   0.02173   0.01223  -0.0503   0.3489   1.0000
   7.500   1.1978   0.02225   0.01272  -0.0497   0.3398   1.0000
   7.750   1.2197   0.02283   0.01332  -0.0491   0.3310   1.0000
   8.000   1.2412   0.02341   0.01386  -0.0485   0.3226   1.0000
   8.250   1.2620   0.02407   0.01455  -0.0478   0.3137   1.0000
   8.500   1.2826   0.02470   0.01515  -0.0471   0.3057   1.0000
   8.750   1.3022   0.02543   0.01596  -0.0464   0.2974   1.0000
   9.000   1.3216   0.02613   0.01662  -0.0456   0.2898   1.0000
   9.250   1.3398   0.02692   0.01750  -0.0449   0.2820   1.0000
   9.500   1.3576   0.02768   0.01830  -0.0440   0.2749   1.0000
   9.750   1.3745   0.02852   0.01921  -0.0431   0.2681   1.0000
  10.000   1.3904   0.02940   0.02017  -0.0422   0.2616   1.0000
  10.250   1.4065   0.03023   0.02099  -0.0412   0.2560   1.0000
  10.500   1.4192   0.03128   0.02222  -0.0402   0.2499   1.0000
  10.750   1.4310   0.03227   0.02329  -0.0389   0.2449   1.0000
  11.000   1.4442   0.03325   0.02428  -0.0378   0.2404   1.0000
  11.250   1.4525   0.03462   0.02584  -0.0367   0.2352   1.0000
  11.500   1.4615   0.03597   0.02729  -0.0358   0.2303   1.0000
  11.750   1.4733   0.03713   0.02846  -0.0350   0.2260   1.0000
  12.000   1.4773   0.03905   0.03058  -0.0345   0.2207   1.0000
  12.250   1.4820   0.04092   0.03256  -0.0340   0.2152   1.0000
  12.500   1.4885   0.04260   0.03425  -0.0335   0.2101   1.0000
  12.750   1.4875   0.04520   0.03706  -0.0335   0.2041   1.0000
  13.000   1.4890   0.04745   0.03940  -0.0333   0.1984   1.0000
  13.250   1.4884   0.05004   0.04209  -0.0333   0.1928   1.0000
  13.500   1.4848   0.05304   0.04524  -0.0334   0.1869   1.0000
  13.750   1.4858   0.05538   0.04757  -0.0333   0.1816   1.0000
  14.000   1.4791   0.05894   0.05135  -0.0337   0.1764   1.0000
  14.250   1.4738   0.06227   0.05481  -0.0340   0.1713   1.0000
  14.500   1.4728   0.06499   0.05752  -0.0341   0.1666   1.0000
  14.750   1.4619   0.06931   0.06208  -0.0349   0.1618   1.0000
  15.000   1.4539   0.07331   0.06622  -0.0357   0.1571   1.0000
  15.250   1.4521   0.07641   0.06932  -0.0362   0.1527   1.0000
  15.500   1.4376   0.08179   0.07495  -0.0377   0.1483   1.0000
  15.750   1.4253   0.08689   0.08020  -0.0392   0.1439   1.0000
  16.000   1.4207   0.09075   0.08409  -0.0403   0.1397   1.0000
  16.250   1.4028   0.09708   0.09063  -0.0424   0.1358   1.0000
  16.500   1.3836   0.10378   0.09750  -0.0449   0.1319   1.0000
  16.750   1.3745   0.10878   0.10256  -0.0468   0.1278   1.0000
  17.000   1.3570   0.11546   0.10937  -0.0495   0.1241   1.0000
  17.250   1.3304   0.12412   0.11820  -0.0532   0.1206   1.0000
  17.500   1.3187   0.13001   0.12418  -0.0559   0.1165   1.0000
  17.750   1.3109   0.13526   0.12949  -0.0583   0.1127   1.0000
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