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GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il)
Reynolds number: 500,000
Max Cl/Cd: 106.69 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe323-il-500000.txt
Download as CSV file: xf-goe323-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3366   0.09923   0.09580  -0.0007   0.6434   0.0275
  -8.250  -0.3419   0.09435   0.09092  -0.0098   0.6410   0.0284
  -8.000  -0.3391   0.09003   0.08660  -0.0155   0.6380   0.0284
  -7.750  -0.3310   0.08628   0.08286  -0.0156   0.6343   0.0286
  -7.500  -0.3198   0.08349   0.08007  -0.0154   0.6305   0.0288
  -7.250  -0.3079   0.08064   0.07720  -0.0167   0.6271   0.0290
  -7.000  -0.2952   0.07766   0.07418  -0.0190   0.6240   0.0292
  -6.750  -0.2811   0.07447   0.07097  -0.0221   0.6210   0.0296
  -6.500  -0.2654   0.07107   0.06756  -0.0258   0.6179   0.0301
  -6.250  -0.2478   0.06747   0.06392  -0.0299   0.6147   0.0309
  -6.000  -0.2100   0.05881   0.05491  -0.0453   0.6125   0.0330
  -5.750  -0.1965   0.05508   0.05116  -0.0460   0.6097   0.0333
  -5.500  -0.1788   0.05272   0.04874  -0.0466   0.6067   0.0335
  -5.250  -0.1588   0.05042   0.04641  -0.0475   0.6037   0.0338
  -5.000  -0.1369   0.04804   0.04398  -0.0487   0.6005   0.0343
  -4.750  -0.1133   0.04552   0.04138  -0.0502   0.5976   0.0350
  -4.500  -0.0742   0.04054   0.03582  -0.0540   0.5952   0.0383
  -4.250  -0.0545   0.03667   0.03189  -0.0550   0.5927   0.0388
  -4.000  -0.0318   0.03494   0.03010  -0.0553   0.5900   0.0391
  -3.750  -0.0076   0.03336   0.02846  -0.0557   0.5873   0.0396
  -3.500   0.0178   0.03171   0.02674  -0.0561   0.5844   0.0404
  -3.250   0.0445   0.02990   0.02479  -0.0565   0.5813   0.0418
  -3.000   0.0752   0.02646   0.02074  -0.0565   0.5784   0.0452
  -2.750   0.1005   0.02493   0.01917  -0.0567   0.5748   0.0457
  -2.500   0.1266   0.02386   0.01804  -0.0568   0.5708   0.0466
  -2.250   0.1538   0.02278   0.01689  -0.0568   0.5669   0.0482
  -2.000   0.1836   0.02142   0.01499  -0.0563   0.5633   0.0527
  -1.750   0.2101   0.01993   0.01352  -0.0565   0.5602   0.0537
  -1.500   0.2374   0.01907   0.01259  -0.0565   0.5572   0.0551
  -1.250   0.2656   0.01839   0.01179  -0.0564   0.5541   0.0578
  -0.250   0.3820   0.01392   0.00636  -0.0548   0.5414   0.0449
   0.000   0.4103   0.01343   0.00580  -0.0546   0.5381   0.0448
   0.250   0.4385   0.01272   0.00510  -0.0545   0.5346   0.0451
   0.500   0.4664   0.01216   0.00457  -0.0543   0.5307   0.0457
   0.750   0.4944   0.01180   0.00422  -0.0542   0.5270   0.0466
   1.000   0.5223   0.01163   0.00402  -0.0540   0.5230   0.0483
   1.250   0.5506   0.01141   0.00384  -0.0539   0.5189   0.0501
   1.500   0.5789   0.01119   0.00363  -0.0538   0.5140   0.0513
   1.750   0.6068   0.01092   0.00335  -0.0537   0.5092   0.0531
   2.000   0.6349   0.01076   0.00320  -0.0536   0.5045   0.0560
   2.250   0.6634   0.01063   0.00312  -0.0536   0.4993   0.0598
   2.500   0.6917   0.01049   0.00298  -0.0535   0.4941   0.0663
   2.750   0.7198   0.01042   0.00291  -0.0534   0.4888   0.0795
   3.000   0.7526   0.00833   0.00303  -0.0548   0.4824   1.0000
   3.250   0.7803   0.00840   0.00301  -0.0546   0.4762   1.0000
   3.500   0.8082   0.00846   0.00304  -0.0545   0.4696   1.0000
   3.750   0.8360   0.00852   0.00307  -0.0544   0.4619   1.0000
   4.000   0.8637   0.00860   0.00311  -0.0543   0.4538   1.0000
   4.250   0.8913   0.00869   0.00315  -0.0542   0.4440   1.0000
   4.500   0.9189   0.00879   0.00322  -0.0541   0.4315   1.0000
   4.750   0.9461   0.00892   0.00329  -0.0540   0.4159   1.0000
   5.000   0.9730   0.00912   0.00340  -0.0538   0.3980   1.0000
   5.250   0.9994   0.00938   0.00356  -0.0537   0.3801   1.0000
   5.500   1.0257   0.00967   0.00376  -0.0535   0.3633   1.0000
   5.750   1.0517   0.00999   0.00400  -0.0533   0.3482   1.0000
   6.000   1.0774   0.01034   0.00427  -0.0531   0.3347   1.0000
   6.250   1.1035   0.01066   0.00454  -0.0530   0.3226   1.0000
   6.500   1.1294   0.01098   0.00482  -0.0528   0.3116   1.0000
   6.750   1.1549   0.01134   0.00513  -0.0526   0.3016   1.0000
   7.000   1.1808   0.01164   0.00542  -0.0525   0.2925   1.0000
   7.250   1.2064   0.01198   0.00574  -0.0523   0.2841   1.0000
   7.500   1.2319   0.01231   0.00605  -0.0522   0.2759   1.0000
   7.750   1.2572   0.01265   0.00638  -0.0520   0.2688   1.0000
   8.000   1.2825   0.01298   0.00671  -0.0518   0.2615   1.0000
   8.250   1.3071   0.01337   0.00709  -0.0515   0.2548   1.0000
   8.500   1.3323   0.01369   0.00743  -0.0514   0.2473   1.0000
   8.750   1.3563   0.01411   0.00782  -0.0511   0.2392   1.0000
   9.000   1.3807   0.01447   0.00820  -0.0509   0.2312   1.0000
   9.250   1.4041   0.01491   0.00863  -0.0505   0.2246   1.0000
   9.500   1.4282   0.01528   0.00902  -0.0503   0.2178   1.0000
   9.750   1.4502   0.01581   0.00953  -0.0499   0.2110   1.0000
  10.000   1.4740   0.01616   0.00994  -0.0496   0.2050   1.0000
  10.250   1.4953   0.01672   0.01048  -0.0491   0.1983   1.0000
  10.500   1.5176   0.01716   0.01097  -0.0487   0.1926   1.0000
  10.750   1.5380   0.01773   0.01155  -0.0482   0.1854   1.0000
  11.000   1.5583   0.01829   0.01213  -0.0476   0.1787   1.0000
  11.250   1.5768   0.01894   0.01280  -0.0469   0.1715   1.0000
  11.500   1.5946   0.01962   0.01350  -0.0461   0.1647   1.0000
  11.750   1.6094   0.02043   0.01433  -0.0451   0.1573   1.0000
  12.000   1.6217   0.02132   0.01525  -0.0438   0.1501   1.0000
  12.250   1.6288   0.02273   0.01666  -0.0428   0.1411   1.0000
  12.500   1.6377   0.02425   0.01820  -0.0424   0.1311   1.0000
  12.750   1.6428   0.02638   0.02033  -0.0424   0.1195   1.0000
  13.000   1.6438   0.02910   0.02301  -0.0426   0.1067   1.0000
  13.250   1.6408   0.03217   0.02604  -0.0426   0.0956   1.0000
  13.500   1.6371   0.03522   0.02908  -0.0425   0.0875   1.0000
  13.750   1.6320   0.03838   0.03226  -0.0423   0.0808   1.0000
  14.000   1.6256   0.04166   0.03555  -0.0420   0.0738   1.0000
  14.250   1.6178   0.04511   0.03900  -0.0418   0.0639   1.0000
  14.500   1.6009   0.04956   0.04339  -0.0416   0.0471   1.0000
  14.750   1.5761   0.05498   0.04872  -0.0417   0.0330   1.0000
  15.000   1.5590   0.05988   0.05365  -0.0420   0.0273   1.0000
  15.250   1.5465   0.06445   0.05829  -0.0426   0.0246   1.0000
  15.500   1.5385   0.06858   0.06252  -0.0431   0.0232   1.0000
  15.750   1.5292   0.07299   0.06701  -0.0438   0.0222   1.0000
  16.000   1.5185   0.07767   0.07180  -0.0447   0.0214   1.0000
  16.250   1.5064   0.08270   0.07693  -0.0458   0.0207   1.0000
  16.500   1.4977   0.08731   0.08165  -0.0468   0.0202   1.0000
  16.750   1.4875   0.09221   0.08668  -0.0480   0.0198   1.0000
  17.000   1.4763   0.09738   0.09196  -0.0495   0.0194   1.0000
  17.250   1.4639   0.10282   0.09752  -0.0511   0.0191   1.0000
  17.500   1.4505   0.10849   0.10330  -0.0528   0.0187   1.0000
  17.750   1.4368   0.11432   0.10924  -0.0548   0.0185   1.0000
  18.000   1.4227   0.12032   0.11535  -0.0570   0.0182   1.0000
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