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GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il)
Reynolds number: 200,000
Max Cl/Cd: 75.72 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe323-il-200000.txt
Download as CSV file: xf-goe323-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3263   0.10531   0.10122  -0.0036   0.7310   0.0435
  -8.500  -0.3289   0.10274   0.09865  -0.0103   0.7263   0.0444
  -8.250  -0.3313   0.09965   0.09553  -0.0186   0.7221   0.0446
  -8.000  -0.3181   0.09518   0.09108  -0.0163   0.7169   0.0449
  -7.750  -0.3039   0.09197   0.08783  -0.0138   0.7118   0.0455
  -7.500  -0.2932   0.08911   0.08494  -0.0140   0.7074   0.0462
  -7.250  -0.2849   0.08629   0.08211  -0.0157   0.7031   0.0471
  -7.000  -0.2749   0.08315   0.07898  -0.0188   0.6984   0.0481
  -6.750  -0.2625   0.07970   0.07550  -0.0232   0.6941   0.0494
  -6.500  -0.2364   0.07469   0.07022  -0.0407   0.6909   0.0519
  -6.250  -0.2219   0.07011   0.06558  -0.0433   0.6876   0.0523
  -6.000  -0.2090   0.06702   0.06256  -0.0421   0.6834   0.0528
  -5.750  -0.1935   0.06434   0.05988  -0.0422   0.6795   0.0535
  -5.500  -0.1756   0.06168   0.05716  -0.0434   0.6761   0.0547
  -5.250  -0.1549   0.05891   0.05427  -0.0456   0.6730   0.0568
  -5.000  -0.1174   0.05456   0.04943  -0.0542   0.6693   0.0612
  -4.750  -0.1007   0.05135   0.04631  -0.0542   0.6653   0.0619
  -4.500  -0.0812   0.04903   0.04399  -0.0544   0.6619   0.0630
  -4.250  -0.0590   0.04687   0.04175  -0.0551   0.6589   0.0648
  -4.000  -0.0329   0.04470   0.03937  -0.0565   0.6562   0.0683
  -3.750  -0.0027   0.04155   0.03588  -0.0589   0.6526   0.0727
  -3.500   0.0195   0.03955   0.03392  -0.0592   0.6487   0.0744
  -3.250   0.0443   0.03797   0.03227  -0.0595   0.6454   0.0780
  -3.000   0.0734   0.03589   0.02980  -0.0605   0.6425   0.0857
  -2.750   0.0970   0.03429   0.02817  -0.0605   0.6397   0.0884
  -2.500   0.1275   0.03335   0.02685  -0.0611   0.6358   0.0990
  -2.250   0.1511   0.03124   0.02485  -0.0613   0.6311   0.1019
  -2.000   0.1795   0.03050   0.02375  -0.0613   0.6265   0.1147
  -1.750   0.2035   0.02868   0.02194  -0.0612   0.6227   0.1190
  -1.500   0.2307   0.02763   0.02080  -0.0614   0.6176   0.1334
  -1.250   0.2572   0.02667   0.01976  -0.0615   0.6132   0.1497
  -1.000   0.2828   0.02562   0.01868  -0.0614   0.6094   0.1686
  -0.500   0.3534   0.02208   0.01383  -0.0594   0.6025   0.0829
  -0.250   0.3819   0.02039   0.01203  -0.0592   0.5978   0.0761
   0.000   0.4113   0.01983   0.01116  -0.0586   0.5938   0.0721
   0.250   0.4391   0.01899   0.01026  -0.0583   0.5903   0.0735
   0.500   0.4669   0.01851   0.00977  -0.0581   0.5858   0.0745
   0.750   0.4947   0.01803   0.00931  -0.0578   0.5805   0.0747
   1.000   0.5224   0.01755   0.00882  -0.0574   0.5761   0.0758
   1.250   0.5500   0.01718   0.00839  -0.0569   0.5725   0.0778
   1.500   0.5772   0.01697   0.00828  -0.0567   0.5662   0.0817
   1.750   0.6045   0.01659   0.00793  -0.0564   0.5609   0.0866
   2.000   0.6324   0.01629   0.00756  -0.0560   0.5566   0.0931
   2.250   0.6597   0.01612   0.00748  -0.0558   0.5501   0.1059
   2.500   0.6947   0.01385   0.00729  -0.0569   0.5438   1.0000
   2.750   0.7226   0.01384   0.00701  -0.0564   0.5391   1.0000
   3.000   0.7492   0.01391   0.00709  -0.0562   0.5309   1.0000
   3.250   0.7768   0.01386   0.00690  -0.0558   0.5249   1.0000
   3.500   0.8038   0.01391   0.00692  -0.0555   0.5175   1.0000
   3.750   0.8311   0.01389   0.00683  -0.0552   0.5102   1.0000
   4.000   0.8583   0.01392   0.00680  -0.0549   0.5030   1.0000
   4.250   0.8854   0.01391   0.00677  -0.0546   0.4942   1.0000
   4.500   0.9123   0.01393   0.00675  -0.0543   0.4855   1.0000
   4.750   0.9394   0.01391   0.00667  -0.0539   0.4763   1.0000
   5.000   0.9660   0.01397   0.00675  -0.0537   0.4654   1.0000
   5.250   0.9928   0.01401   0.00673  -0.0534   0.4553   1.0000
   5.500   1.0193   0.01407   0.00675  -0.0530   0.4438   1.0000
   5.750   1.0455   0.01420   0.00688  -0.0528   0.4306   1.0000
   6.000   1.0714   0.01435   0.00701  -0.0524   0.4170   1.0000
   6.250   1.0970   0.01455   0.00715  -0.0521   0.4030   1.0000
   6.500   1.1222   0.01482   0.00736  -0.0517   0.3890   1.0000
   6.750   1.1469   0.01516   0.00762  -0.0513   0.3758   1.0000
   7.000   1.1713   0.01557   0.00793  -0.0509   0.3637   1.0000
   7.250   1.1954   0.01602   0.00832  -0.0505   0.3521   1.0000
   7.500   1.2194   0.01649   0.00880  -0.0502   0.3411   1.0000
   7.750   1.2429   0.01703   0.00926  -0.0497   0.3311   1.0000
   8.000   1.2661   0.01756   0.00975  -0.0493   0.3213   1.0000
   8.250   1.2894   0.01809   0.01032  -0.0488   0.3121   1.0000
   8.500   1.3122   0.01870   0.01084  -0.0484   0.3042   1.0000
   8.750   1.3350   0.01923   0.01146  -0.0479   0.2962   1.0000
   9.000   1.3574   0.01984   0.01201  -0.0474   0.2888   1.0000
   9.250   1.3793   0.02040   0.01268  -0.0469   0.2812   1.0000
   9.500   1.4011   0.02099   0.01327  -0.0464   0.2748   1.0000
   9.750   1.4226   0.02165   0.01396  -0.0459   0.2687   1.0000
  10.000   1.4431   0.02221   0.01463  -0.0452   0.2620   1.0000
  10.250   1.4635   0.02290   0.01527  -0.0446   0.2556   1.0000
  10.500   1.4815   0.02348   0.01601  -0.0438   0.2483   1.0000
  10.750   1.4998   0.02418   0.01664  -0.0429   0.2416   1.0000
  11.000   1.5154   0.02486   0.01752  -0.0419   0.2347   1.0000
  11.250   1.5308   0.02560   0.01827  -0.0409   0.2285   1.0000
  11.500   1.5443   0.02644   0.01921  -0.0397   0.2224   1.0000
  11.750   1.5535   0.02733   0.02020  -0.0382   0.2162   1.0000
  12.000   1.5629   0.02840   0.02126  -0.0368   0.2104   1.0000
  12.250   1.5694   0.02971   0.02276  -0.0359   0.2042   1.0000
  12.500   1.5761   0.03117   0.02423  -0.0352   0.1984   1.0000
  12.750   1.5821   0.03286   0.02606  -0.0348   0.1924   1.0000
  13.000   1.5868   0.03477   0.02806  -0.0346   0.1860   1.0000
  13.250   1.5909   0.03679   0.03013  -0.0344   0.1802   1.0000
  13.500   1.5944   0.03899   0.03248  -0.0345   0.1740   1.0000
  13.750   1.5959   0.04128   0.03475  -0.0343   0.1686   1.0000
  14.000   1.5976   0.04373   0.03740  -0.0344   0.1625   1.0000
  14.250   1.5960   0.04645   0.04015  -0.0345   0.1565   1.0000
  14.500   1.5952   0.04917   0.04299  -0.0346   0.1505   1.0000
  14.750   1.5926   0.05211   0.04601  -0.0348   0.1446   1.0000
  15.000   1.5889   0.05518   0.04917  -0.0349   0.1392   1.0000
  15.250   1.5845   0.05846   0.05257  -0.0353   0.1325   1.0000
  15.500   1.5788   0.06200   0.05617  -0.0358   0.1269   1.0000
  15.750   1.5729   0.06580   0.06007  -0.0366   0.1195   1.0000
  16.000   1.5642   0.07003   0.06436  -0.0375   0.1119   1.0000
  16.500   1.5385   0.07998   0.07440  -0.0400   0.0965   1.0000
  16.750   1.5228   0.08551   0.07997  -0.0415   0.0898   1.0000
  17.000   1.5044   0.09158   0.08608  -0.0433   0.0836   1.0000
  17.250   1.4877   0.09757   0.09216  -0.0451   0.0765   1.0000
  17.500   1.4684   0.10410   0.09875  -0.0473   0.0704   1.0000
  17.750   1.4491   0.11082   0.10555  -0.0498   0.0628   1.0000
  18.000   1.4300   0.11767   0.11246  -0.0524   0.0543   1.0000
  18.250   1.4097   0.12482   0.11966  -0.0554   0.0485   1.0000
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