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GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
Reynolds number: 100,000
Max Cl/Cd: 55.24 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe319-il-100000-n5.txt
Download as CSV file: xf-goe319-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 319 (HANSA-BRANDENBURG II) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2488   0.11501   0.10994  -0.0283   1.0000   0.0507
  -9.500  -0.2477   0.11299   0.10798  -0.0307   1.0000   0.0512
  -9.250  -0.2491   0.11119   0.10626  -0.0332   1.0000   0.0514
  -9.000  -0.2402   0.10760   0.10274  -0.0329   1.0000   0.0517
  -8.750  -0.2306   0.10431   0.09949  -0.0321   1.0000   0.0523
  -8.500  -0.2273   0.10199   0.09725  -0.0316   1.0000   0.0530
  -8.250  -0.2207   0.09949   0.09482  -0.0326   0.9943   0.0539
  -8.000  -0.2024   0.09602   0.09135  -0.0371   0.9791   0.0558
  -7.750  -0.1875   0.09301   0.08834  -0.0450   0.9590   0.0581
  -7.500  -0.1714   0.08983   0.08512  -0.0573   0.9374   0.0587
  -7.250  -0.1537   0.08557   0.08087  -0.0546   0.9288   0.0594
  -7.000  -0.1367   0.08226   0.07755  -0.0556   0.9162   0.0604
  -6.750  -0.1206   0.07923   0.07449  -0.0580   0.9029   0.0616
  -6.500  -0.1048   0.07628   0.07149  -0.0611   0.8897   0.0632
  -6.250  -0.0886   0.07343   0.06858  -0.0656   0.8751   0.0654
  -6.000  -0.0612   0.07082   0.06567  -0.0778   0.8595   0.0671
  -5.750  -0.0501   0.06713   0.06205  -0.0758   0.8491   0.0677
  -5.500  -0.0367   0.06433   0.05925  -0.0743   0.8394   0.0689
  -5.250  -0.0198   0.06187   0.05677  -0.0750   0.8279   0.0712
  -5.000   0.0048   0.05936   0.05409  -0.0789   0.8181   0.0754
  -4.750   0.0361   0.05669   0.05108  -0.0850   0.8077   0.0775
  -4.500   0.0515   0.05360   0.04802  -0.0843   0.7986   0.0784
  -4.250   0.0704   0.05112   0.04550  -0.0844   0.7896   0.0799
  -4.000   0.0924   0.04887   0.04316  -0.0852   0.7806   0.0820
  -3.750   0.1296   0.04782   0.04158  -0.0891   0.7721   0.0887
  -3.500   0.1516   0.04481   0.03846  -0.0898   0.7640   0.0896
  -3.250   0.1716   0.04218   0.03583  -0.0897   0.7557   0.0908
  -3.000   0.1938   0.04021   0.03381  -0.0897   0.7480   0.0934
  -2.750   0.2254   0.03916   0.03232  -0.0910   0.7394   0.1029
  -2.500   0.2583   0.03357   0.02616  -0.0914   0.7338   0.0592
  -2.250   0.2829   0.03200   0.02450  -0.0913   0.7249   0.0568
  -2.000   0.3099   0.03018   0.02241  -0.0912   0.7177   0.0547
  -1.750   0.3401   0.02779   0.01937  -0.0909   0.7104   0.0513
  -1.500   0.3665   0.02653   0.01792  -0.0906   0.7021   0.0510
  -1.250   0.3942   0.02528   0.01627  -0.0901   0.6938   0.0514
  -1.000   0.4195   0.02445   0.01542  -0.0897   0.6829   0.0527
  -0.750   0.4456   0.02357   0.01433  -0.0890   0.6703   0.0535
  -0.500   0.4725   0.02259   0.01305  -0.0882   0.6581   0.0534
  -0.250   0.4991   0.02174   0.01198  -0.0875   0.6455   0.0534
   0.000   0.5257   0.02105   0.01114  -0.0869   0.6343   0.0538
   0.250   0.5530   0.02043   0.01035  -0.0863   0.6262   0.0543
   0.500   0.5794   0.01993   0.00981  -0.0857   0.6159   0.0552
   0.750   0.6063   0.01952   0.00926  -0.0851   0.6073   0.0575
   1.000   0.6323   0.01915   0.00889  -0.0846   0.5970   0.0598
   1.250   0.6584   0.01882   0.00856  -0.0840   0.5881   0.0618
   1.500   0.6843   0.01854   0.00825  -0.0833   0.5782   0.0639
   1.750   0.7102   0.01835   0.00798  -0.0826   0.5681   0.0665
   2.000   0.7365   0.01819   0.00776  -0.0820   0.5579   0.0709
   2.250   0.7626   0.01813   0.00767  -0.0815   0.5459   0.0791
   2.500   0.7889   0.01805   0.00754  -0.0809   0.5344   0.0929
   2.750   0.8153   0.01768   0.00749  -0.0806   0.5229   0.2383
   3.250   0.8749   0.01660   0.00761  -0.0811   0.4959   1.0000
   3.500   0.8993   0.01684   0.00770  -0.0804   0.4820   1.0000
   3.750   0.9233   0.01709   0.00783  -0.0795   0.4667   1.0000
   4.000   0.9469   0.01737   0.00798  -0.0787   0.4498   1.0000
   4.250   0.9701   0.01767   0.00817  -0.0778   0.4317   1.0000
   4.500   0.9929   0.01800   0.00839  -0.0769   0.4131   1.0000
   4.750   1.0154   0.01838   0.00863  -0.0759   0.3951   1.0000
   5.000   1.0374   0.01880   0.00891  -0.0749   0.3784   1.0000
   5.250   1.0591   0.01926   0.00923  -0.0739   0.3630   1.0000
   5.500   1.0805   0.01976   0.00961  -0.0729   0.3495   1.0000
   5.750   1.1017   0.02029   0.01001  -0.0719   0.3376   1.0000
   6.000   1.1233   0.02081   0.01047  -0.0710   0.3272   1.0000
   6.250   1.1444   0.02139   0.01094  -0.0700   0.3186   1.0000
   6.500   1.1658   0.02193   0.01146  -0.0691   0.3098   1.0000
   6.750   1.1865   0.02254   0.01195  -0.0681   0.3024   1.0000
   7.000   1.2077   0.02309   0.01254  -0.0673   0.2947   1.0000
   7.250   1.2281   0.02371   0.01307  -0.0663   0.2882   1.0000
   7.500   1.2490   0.02431   0.01368  -0.0654   0.2821   1.0000
   7.750   1.2695   0.02491   0.01431  -0.0645   0.2761   1.0000
   8.000   1.2898   0.02557   0.01490  -0.0636   0.2711   1.0000
   8.250   1.3102   0.02621   0.01559  -0.0627   0.2661   1.0000
   8.500   1.3300   0.02686   0.01630  -0.0617   0.2609   1.0000
   8.750   1.3495   0.02753   0.01699  -0.0607   0.2563   1.0000
   9.000   1.3704   0.02826   0.01765  -0.0600   0.2524   1.0000
   9.250   1.3887   0.02898   0.01852  -0.0589   0.2482   1.0000
   9.500   1.4068   0.02972   0.01937  -0.0578   0.2437   1.0000
   9.750   1.4246   0.03046   0.02015  -0.0567   0.2395   1.0000
  10.000   1.4443   0.03125   0.02088  -0.0559   0.2356   1.0000
  10.250   1.4581   0.03209   0.02189  -0.0543   0.2314   1.0000
  10.500   1.4718   0.03295   0.02290  -0.0528   0.2272   1.0000
  10.750   1.4867   0.03382   0.02384  -0.0514   0.2234   1.0000
  11.000   1.5031   0.03468   0.02472  -0.0503   0.2200   1.0000
  11.250   1.5178   0.03568   0.02579  -0.0491   0.2164   1.0000
  11.500   1.5262   0.03683   0.02716  -0.0472   0.2124   1.0000
  11.750   1.5359   0.03795   0.02840  -0.0456   0.2084   1.0000
  12.000   1.5477   0.03899   0.02950  -0.0443   0.2048   1.0000
  12.250   1.5627   0.03999   0.03048  -0.0433   0.2014   1.0000
  12.500   1.5629   0.04166   0.03245  -0.0413   0.1974   1.0000
  12.750   1.5659   0.04324   0.03420  -0.0398   0.1932   1.0000
  13.000   1.5721   0.04462   0.03566  -0.0385   0.1894   1.0000
  13.250   1.5830   0.04578   0.03679  -0.0375   0.1861   1.0000
  13.500   1.5780   0.04821   0.03953  -0.0361   0.1823   1.0000
  13.750   1.5770   0.05045   0.04196  -0.0351   0.1786   1.0000
  14.000   1.5795   0.05242   0.04406  -0.0342   0.1753   1.0000
  14.250   1.5859   0.05404   0.04572  -0.0335   0.1725   1.0000
  14.500   1.5812   0.05690   0.04879  -0.0329   0.1695   1.0000
  14.750   1.5723   0.06033   0.05246  -0.0326   0.1662   1.0000
  15.000   1.5671   0.06341   0.05571  -0.0324   0.1631   1.0000
  15.250   1.5667   0.06597   0.05836  -0.0322   0.1604   1.0000
  15.500   1.5721   0.06788   0.06030  -0.0318   0.1579   1.0000
  15.750   1.5476   0.07374   0.06648  -0.0328   0.1551   1.0000
  16.000   1.5252   0.07968   0.07267  -0.0341   0.1522   1.0000
  16.250   1.5096   0.08490   0.07805  -0.0355   0.1494   1.0000
  16.500   1.5102   0.08774   0.08095  -0.0360   0.1467   1.0000
  16.750   1.5008   0.09222   0.08553  -0.0372   0.1442   1.0000
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