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GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)
Reynolds number: 50,000
Max Cl/Cd: 28.94 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe314-il-50000.txt
Download as CSV file: xf-goe314-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 314 (HANSA-BRANDENBURG) AIRFOIL             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3258   0.11253   0.10536  -0.0200   1.0000   0.1202
  -8.750  -0.3304   0.11160   0.10453  -0.0215   1.0000   0.1237
  -8.500  -0.3439   0.11203   0.10512  -0.0233   1.0000   0.1248
  -8.250  -0.3187   0.10467   0.09774  -0.0212   1.0000   0.1299
  -8.000  -0.3156   0.10216   0.09530  -0.0211   1.0000   0.1347
  -7.750  -0.3238   0.10119   0.09446  -0.0216   1.0000   0.1383
  -7.500  -0.3384   0.10141   0.09484  -0.0241   1.0000   0.1398
  -7.250  -0.3233   0.09567   0.08915  -0.0211   1.0000   0.1435
  -7.000  -0.3177   0.09272   0.08626  -0.0201   1.0000   0.1490
  -6.750  -0.3227   0.09146   0.08511  -0.0218   1.0000   0.1539
  -6.500  -0.3281   0.09019   0.08394  -0.0246   1.0000   0.1566
  -6.250  -0.3166   0.08549   0.07930  -0.0201   1.0000   0.1624
  -6.000  -0.3188   0.08406   0.07795  -0.0213   1.0000   0.1697
  -5.750  -0.3190   0.08142   0.07540  -0.0211   1.0000   0.1740
  -5.500  -0.3161   0.07884   0.07290  -0.0188   1.0000   0.1826
  -5.250  -0.3178   0.07701   0.07111  -0.0198   1.0000   0.1893
  -5.000  -0.3158   0.07455   0.06873  -0.0173   1.0000   0.1990
  -4.750  -0.3149   0.07217   0.06640  -0.0167   1.0000   0.2068
  -4.500  -0.3114   0.07057   0.06477  -0.0181   1.0000   0.2194
  -4.250  -0.3088   0.06784   0.06212  -0.0149   1.0000   0.2296
  -4.000  -0.3052   0.06540   0.05973  -0.0138   1.0000   0.2419
  -3.750  -0.2985   0.06381   0.05809  -0.0147   1.0000   0.2639
  -3.500   0.1142   0.03773   0.03150  -0.0282   1.0000   1.0000
  -3.250   0.1200   0.03657   0.03047  -0.0278   1.0000   1.0000
  -2.250  -0.2993   0.05087   0.04581   0.0062   1.0000   0.4658
  -2.000  -0.3001   0.04893   0.04402   0.0112   0.9982   0.5143
  -1.750  -0.2734   0.04609   0.04129   0.0131   0.9820   0.5904
  -1.500  -0.2435   0.04333   0.03861   0.0137   0.9640   0.6428
  -1.250  -0.1978   0.04061   0.03586   0.0091   0.9453   0.6786
  -1.000  -0.1210   0.03779   0.03284  -0.0055   0.9254   0.6787
  -0.750   0.1121   0.03717   0.02974  -0.0611   0.8985   0.3611
  -0.500   0.1937   0.03596   0.02760  -0.0698   0.8808   0.2599
  -0.250   0.2606   0.03483   0.02574  -0.0750   0.8641   0.2166
   0.000   0.3095   0.03391   0.02437  -0.0775   0.8449   0.2028
   0.250   0.3577   0.03240   0.02268  -0.0800   0.8271   0.1936
   0.500   0.4024   0.03164   0.02154  -0.0814   0.8094   0.1859
   0.750   0.4464   0.03069   0.02037  -0.0827   0.7920   0.1849
   1.000   0.4900   0.02984   0.01935  -0.0841   0.7747   0.1905
   1.250   0.5277   0.02918   0.01859  -0.0844   0.7576   0.1946
   1.500   0.5603   0.02877   0.01807  -0.0839   0.7410   0.2008
   1.750   0.5890   0.02840   0.01771  -0.0831   0.7247   0.2161
   2.000   0.6161   0.02811   0.01747  -0.0821   0.7089   0.2365
   2.250   0.6419   0.02771   0.01740  -0.0811   0.6936   0.2894
   2.500   0.6907   0.02637   0.01701  -0.0831   0.6771   1.0000
   2.750   0.7154   0.02683   0.01709  -0.0816   0.6618   1.0000
   3.000   0.7395   0.02728   0.01730  -0.0802   0.6465   1.0000
   3.250   0.7631   0.02778   0.01762  -0.0789   0.6314   1.0000
   3.500   0.7866   0.02828   0.01800  -0.0775   0.6163   1.0000
   3.750   0.8099   0.02883   0.01843  -0.0762   0.6015   1.0000
   4.000   0.8331   0.02941   0.01892  -0.0749   0.5872   1.0000
   4.250   0.8568   0.03001   0.01943  -0.0737   0.5733   1.0000
   4.500   0.8819   0.03055   0.01989  -0.0726   0.5599   1.0000
   4.750   0.9051   0.03127   0.02056  -0.0714   0.5466   1.0000
   5.000   0.9235   0.03240   0.02172  -0.0700   0.5328   1.0000
   5.250   0.9409   0.03369   0.02309  -0.0687   0.5197   1.0000
   5.500   0.9599   0.03495   0.02438  -0.0675   0.5078   1.0000
   5.750   0.9883   0.03553   0.02487  -0.0667   0.4976   1.0000
   6.000   0.9990   0.03746   0.02697  -0.0652   0.4855   1.0000
   6.250   1.0105   0.03947   0.02913  -0.0637   0.4747   1.0000
   6.500   1.0407   0.04004   0.02964  -0.0632   0.4665   1.0000
   6.750   1.0340   0.04376   0.03365  -0.0613   0.4567   1.0000
   7.000   1.0641   0.04453   0.03442  -0.0608   0.4505   1.0000
   7.250   1.0324   0.05069   0.04087  -0.0586   0.4424   1.0000
   7.500   1.0517   0.05241   0.04266  -0.0578   0.4364   1.0000
   7.750   1.0078   0.06009   0.05044  -0.0565   0.4309   1.0000
   8.000   0.9112   0.07356   0.06380  -0.0580   0.4299   1.0000
   8.250   0.8902   0.08003   0.07027  -0.0595   0.4313   1.0000
   8.500   0.8879   0.08504   0.07533  -0.0608   0.4351   1.0000
   8.750   0.7302   0.10554   0.09576  -0.0747   0.5804   1.0000
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