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GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il)
Reynolds number: 200,000
Max Cl/Cd: 75.17 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe322-il-200000.txt
Download as CSV file: xf-goe322-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 322 (HANSA-BRANDENBURG IV.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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1854   0.10210   0.09835  -0.0392   0.8183   0.0473
  -8.750  -0.1824   0.09935   0.09558  -0.0426   0.8117   0.0494
  -8.500  -0.1923   0.09686   0.09308  -0.0520   0.8052   0.0502
  -8.250  -0.1841   0.09252   0.08876  -0.0525   0.7991   0.0506
  -8.000  -0.1680   0.08936   0.08555  -0.0495   0.7936   0.0512
  -7.750  -0.1566   0.08666   0.08282  -0.0493   0.7882   0.0521
  -7.500  -0.1473   0.08393   0.08009  -0.0506   0.7821   0.0532
  -7.250  -0.1415   0.08129   0.07742  -0.0524   0.7768   0.0546
  -7.000  -0.1317   0.07807   0.07417  -0.0569   0.7716   0.0566
  -6.750  -0.1165   0.07206   0.06799  -0.0744   0.7656   0.0593
  -6.500  -0.1054   0.06926   0.06521  -0.0714   0.7605   0.0600
  -6.250  -0.0915   0.06688   0.06281  -0.0706   0.7556   0.0610
  -6.000  -0.0750   0.06423   0.06015  -0.0720   0.7497   0.0624
  -5.750  -0.0565   0.06130   0.05713  -0.0747   0.7448   0.0647
  -5.500  -0.0251   0.05644   0.05174  -0.0852   0.7408   0.0697
  -5.250  -0.0092   0.05324   0.04865  -0.0849   0.7347   0.0705
  -5.000   0.0089   0.05096   0.04636  -0.0848   0.7294   0.0717
  -4.750   0.0294   0.04890   0.04420  -0.0852   0.7252   0.0740
  -4.500   0.0640   0.04628   0.04100  -0.0899   0.7198   0.0818
  -4.250   0.0829   0.04303   0.03784  -0.0901   0.7144   0.0830
  -4.000   0.1046   0.04098   0.03575  -0.0902   0.7100   0.0847
  -3.750   0.1289   0.03919   0.03387  -0.0907   0.7049   0.0877
  -3.500   0.1601   0.03709   0.03127  -0.0924   0.6992   0.0961
  -3.250   0.1830   0.03487   0.02905  -0.0925   0.6942   0.0980
  -3.000   0.2082   0.03334   0.02745  -0.0926   0.6881   0.1015
  -2.750   0.2368   0.03173   0.02550  -0.0932   0.6812   0.1118
  -2.500   0.2620   0.03022   0.02393  -0.0931   0.6762   0.1161
  -2.250   0.2905   0.02897   0.02243  -0.0935   0.6702   0.1275
  -2.000   0.3298   0.02340   0.01565  -0.0926   0.6656   0.0682
  -1.750   0.3582   0.02177   0.01379  -0.0925   0.6611   0.0662
  -1.500   0.3870   0.02061   0.01238  -0.0924   0.6564   0.0652
  -1.250   0.4157   0.01987   0.01150  -0.0923   0.6501   0.0665
  -1.000   0.4445   0.01913   0.01058  -0.0921   0.6453   0.0673
  -0.750   0.4732   0.01847   0.00977  -0.0920   0.6409   0.0679
  -0.500   0.5014   0.01799   0.00925  -0.0919   0.6343   0.0688
  -0.250   0.5294   0.01724   0.00849  -0.0917   0.6292   0.0708
   0.000   0.5575   0.01681   0.00806  -0.0916   0.6245   0.0742
   0.250   0.5853   0.01656   0.00784  -0.0915   0.6178   0.0800
   0.500   0.6134   0.01612   0.00742  -0.0914   0.6127   0.0896
   0.750   0.6415   0.01572   0.00713  -0.0913   0.6073   0.1200
   1.000   0.6680   0.01493   0.00697  -0.0914   0.6005   0.3075
   1.250   0.7008   0.01327   0.00675  -0.0918   0.5953   1.0000
   1.500   0.7281   0.01339   0.00678  -0.0917   0.5882   1.0000
   1.750   0.7561   0.01343   0.00667  -0.0915   0.5819   1.0000
   2.000   0.7837   0.01349   0.00661  -0.0914   0.5750   1.0000
   2.250   0.8112   0.01353   0.00655  -0.0913   0.5668   1.0000
   2.500   0.8387   0.01359   0.00650  -0.0911   0.5590   1.0000
   2.750   0.8660   0.01364   0.00645  -0.0909   0.5501   1.0000
   3.000   0.8930   0.01373   0.00647  -0.0908   0.5412   1.0000
   3.250   0.9203   0.01379   0.00640  -0.0906   0.5323   1.0000
   3.500   0.9468   0.01392   0.00650  -0.0904   0.5219   1.0000
   3.750   0.9738   0.01404   0.00651  -0.0902   0.5131   1.0000
   4.000   1.0001   0.01419   0.00663  -0.0900   0.5029   1.0000
   4.250   1.0265   0.01438   0.00677  -0.0899   0.4934   1.0000
   4.500   1.0529   0.01456   0.00685  -0.0897   0.4842   1.0000
   4.750   1.0786   0.01476   0.00707  -0.0894   0.4734   1.0000
   5.000   1.1043   0.01498   0.00722  -0.0892   0.4635   1.0000
   5.250   1.1297   0.01520   0.00738  -0.0889   0.4531   1.0000
   5.500   1.1547   0.01545   0.00764  -0.0885   0.4421   1.0000
   5.750   1.1796   0.01573   0.00786  -0.0882   0.4321   1.0000
   6.000   1.2041   0.01602   0.00810  -0.0878   0.4220   1.0000
   6.250   1.2282   0.01634   0.00843  -0.0874   0.4118   1.0000
   6.500   1.2521   0.01670   0.00872  -0.0870   0.4028   1.0000
   6.750   1.2754   0.01705   0.00908  -0.0865   0.3930   1.0000
   7.000   1.2985   0.01746   0.00946  -0.0859   0.3839   1.0000
   7.250   1.3210   0.01789   0.00984  -0.0853   0.3751   1.0000
   7.500   1.3430   0.01832   0.01031  -0.0847   0.3660   1.0000
   7.750   1.3647   0.01884   0.01073  -0.0840   0.3578   1.0000
   8.000   1.3853   0.01931   0.01127  -0.0832   0.3486   1.0000
   8.250   1.4053   0.01987   0.01179  -0.0823   0.3397   1.0000
   8.500   1.4235   0.02041   0.01233  -0.0811   0.3298   1.0000
   8.750   1.4403   0.02099   0.01294  -0.0798   0.3195   1.0000
   9.000   1.4559   0.02165   0.01353  -0.0783   0.3098   1.0000
   9.250   1.4696   0.02227   0.01422  -0.0766   0.2999   1.0000
   9.500   1.4818   0.02297   0.01494  -0.0746   0.2914   1.0000
   9.750   1.4911   0.02372   0.01569  -0.0723   0.2833   1.0000
  10.000   1.5009   0.02455   0.01658  -0.0703   0.2754   1.0000
  10.250   1.5097   0.02550   0.01754  -0.0683   0.2677   1.0000
  10.500   1.5191   0.02651   0.01862  -0.0667   0.2603   1.0000
  10.750   1.5276   0.02765   0.01979  -0.0652   0.2533   1.0000
  11.000   1.5364   0.02888   0.02107  -0.0640   0.2467   1.0000
  11.250   1.5444   0.03021   0.02247  -0.0629   0.2398   1.0000
  11.500   1.5518   0.03168   0.02396  -0.0618   0.2337   1.0000
  11.750   1.5602   0.03314   0.02553  -0.0610   0.2273   1.0000
  12.250   1.5718   0.03659   0.02909  -0.0593   0.2143   1.0000
  12.500   1.5744   0.03863   0.03113  -0.0584   0.2080   1.0000
  12.750   1.5794   0.04055   0.03318  -0.0578   0.2011   1.0000
  13.000   1.5801   0.04286   0.03550  -0.0570   0.1945   1.0000
  13.250   1.5817   0.04517   0.03790  -0.0564   0.1869   1.0000
  13.500   1.5804   0.04777   0.04053  -0.0558   0.1806   1.0000
  13.750   1.5816   0.05021   0.04306  -0.0552   0.1742   1.0000
  14.000   1.5787   0.05315   0.04604  -0.0548   0.1673   1.0000
  14.250   1.5770   0.05611   0.04908  -0.0545   0.1592   1.0000
  14.500   1.5707   0.05968   0.05268  -0.0543   0.1518   1.0000
  14.750   1.5665   0.06317   0.05625  -0.0544   0.1404   1.0000
  15.000   1.5594   0.06712   0.06023  -0.0546   0.1264   1.0000
  15.250   1.5379   0.07299   0.06597  -0.0551   0.0927   1.0000
  15.500   1.5092   0.07994   0.07277  -0.0559   0.0705   1.0000
  15.750   1.4819   0.08688   0.07968  -0.0568   0.0538   1.0000
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