Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)
Reynolds number: 200,000
Max Cl/Cd: 70.53 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe314-il-200000.txt
Download as CSV file: xf-goe314-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3182   0.09545   0.09197  -0.0254   1.0000   0.0398
  -7.750  -0.3285   0.09417   0.09077  -0.0275   1.0000   0.0400
  -7.500  -0.3291   0.09205   0.08868  -0.0311   1.0000   0.0401
  -7.250  -0.3273   0.08838   0.08506  -0.0313   1.0000   0.0403
  -7.000  -0.3219   0.08431   0.08105  -0.0262   1.0000   0.0408
  -6.750  -0.3194   0.08166   0.07845  -0.0239   1.0000   0.0412
  -6.500  -0.3206   0.07952   0.07637  -0.0220   1.0000   0.0418
  -6.250  -0.3264   0.07785   0.07476  -0.0201   1.0000   0.0423
  -6.000  -0.3324   0.07622   0.07317  -0.0185   0.9997   0.0428
  -5.750  -0.2970   0.07173   0.06861  -0.0264   0.9942   0.0444
  -5.500  -0.2398   0.06732   0.06394  -0.0423   0.9855   0.0478
  -5.250  -0.2014   0.06197   0.05840  -0.0506   0.9777   0.0486
  -5.000  -0.1787   0.05766   0.05417  -0.0522   0.9727   0.0494
  -4.750  -0.1503   0.05430   0.05078  -0.0551   0.9655   0.0507
  -4.500  -0.1141   0.05086   0.04725  -0.0599   0.9591   0.0526
  -4.250  -0.0757   0.04766   0.04389  -0.0648   0.9509   0.0556
  -4.000  -0.0244   0.04407   0.03982  -0.0718   0.9443   0.0587
  -3.750   0.0020   0.04060   0.03642  -0.0737   0.9360   0.0600
  -3.500   0.0363   0.03797   0.03375  -0.0766   0.9286   0.0625
  -3.250   0.0707   0.03574   0.03134  -0.0787   0.9171   0.0663
  -3.000   0.1102   0.03340   0.02854  -0.0812   0.9057   0.0709
  -2.750   0.1393   0.03083   0.02598  -0.0826   0.8934   0.0729
  -2.500   0.1687   0.02910   0.02413  -0.0834   0.8788   0.0765
  -2.250   0.2008   0.02798   0.02252  -0.0834   0.8624   0.0841
  -2.000   0.2235   0.02597   0.02054  -0.0832   0.8445   0.0870
  -1.750   0.2521   0.02579   0.01989  -0.0823   0.8255   0.0976
  -1.500   0.2739   0.02355   0.01768  -0.0818   0.8062   0.1004
  -1.250   0.3005   0.02319   0.01693  -0.0808   0.7860   0.1119
  -1.000   0.3224   0.02142   0.01516  -0.0801   0.7638   0.1163
  -0.750   0.3463   0.02052   0.01404  -0.0791   0.7396   0.1293
  -0.500   0.3695   0.01963   0.01298  -0.0781   0.7136   0.1449
  -0.250   0.3924   0.01881   0.01201  -0.0772   0.6861   0.1639
   0.500   0.4786   0.01681   0.00848  -0.0725   0.6091   0.0830
   0.750   0.5037   0.01560   0.00714  -0.0717   0.5871   0.0795
   1.000   0.5291   0.01510   0.00645  -0.0708   0.5676   0.0781
   1.250   0.5543   0.01488   0.00603  -0.0700   0.5492   0.0799
   1.500   0.5794   0.01470   0.00569  -0.0691   0.5321   0.0816
   1.750   0.6045   0.01449   0.00537  -0.0683   0.5166   0.0824
   2.000   0.6291   0.01413   0.00500  -0.0674   0.5032   0.0846
   2.250   0.6537   0.01398   0.00486  -0.0667   0.4916   0.0891
   2.500   0.6788   0.01402   0.00481  -0.0660   0.4810   0.0962
   2.750   0.7032   0.01386   0.00469  -0.0652   0.4700   0.1040
   3.000   0.7281   0.01385   0.00465  -0.0645   0.4597   0.1189
   3.250   0.7819   0.01225   0.00471  -0.0701   0.4471   1.0000
   3.500   0.8061   0.01248   0.00482  -0.0692   0.4375   1.0000
   3.750   0.8302   0.01272   0.00499  -0.0684   0.4278   1.0000
   4.000   0.8542   0.01301   0.00514  -0.0675   0.4182   1.0000
   4.250   0.8778   0.01319   0.00532  -0.0666   0.4072   1.0000
   4.500   0.9015   0.01343   0.00551  -0.0657   0.3970   1.0000
   4.750   0.9252   0.01370   0.00568  -0.0649   0.3874   1.0000
   5.000   0.9489   0.01390   0.00593  -0.0640   0.3772   1.0000
   5.250   0.9723   0.01416   0.00614  -0.0632   0.3670   1.0000
   5.500   0.9954   0.01440   0.00632  -0.0622   0.3562   1.0000
   5.750   1.0186   0.01461   0.00658  -0.0613   0.3450   1.0000
   6.000   1.0417   0.01488   0.00683  -0.0604   0.3347   1.0000
   6.250   1.0645   0.01518   0.00707  -0.0595   0.3248   1.0000
   6.500   1.0876   0.01542   0.00738  -0.0586   0.3144   1.0000
   6.750   1.1103   0.01576   0.00772  -0.0578   0.3052   1.0000
   7.000   1.1329   0.01608   0.00804  -0.0568   0.2961   1.0000
   7.250   1.1557   0.01642   0.00842  -0.0560   0.2873   1.0000
   7.500   1.1779   0.01681   0.00878  -0.0550   0.2797   1.0000
   7.750   1.2005   0.01714   0.00923  -0.0542   0.2716   1.0000
   8.000   1.2221   0.01755   0.00959  -0.0532   0.2642   1.0000
   8.250   1.2443   0.01787   0.01004  -0.0523   0.2564   1.0000
   8.750   1.2864   0.01855   0.01085  -0.0502   0.2396   1.0000
   9.000   1.3064   0.01891   0.01125  -0.0490   0.2304   1.0000
   9.250   1.3255   0.01929   0.01165  -0.0477   0.2204   1.0000
   9.500   1.3452   0.01964   0.01210  -0.0465   0.2092   1.0000
   9.750   1.3636   0.02006   0.01261  -0.0451   0.1972   1.0000
  10.000   1.3807   0.02055   0.01314  -0.0436   0.1828   1.0000
  10.250   1.3954   0.02120   0.01377  -0.0418   0.1646   1.0000
  10.500   1.4080   0.02200   0.01453  -0.0397   0.1371   1.0000
  10.750   1.4074   0.02356   0.01573  -0.0361   0.0894   1.0000
  11.000   1.4038   0.02524   0.01730  -0.0320   0.0761   1.0000
  11.250   1.4018   0.02685   0.01897  -0.0285   0.0693   1.0000
  11.500   1.3950   0.02883   0.02102  -0.0249   0.0636   1.0000
  11.750   1.3874   0.03104   0.02338  -0.0219   0.0585   1.0000
  12.000   1.3703   0.03420   0.02659  -0.0191   0.0549   1.0000
  12.250   1.3636   0.03694   0.02949  -0.0175   0.0505   1.0000
  12.500   1.3554   0.04004   0.03268  -0.0165   0.0473   1.0000
  12.750   1.3423   0.04384   0.03651  -0.0158   0.0450   1.0000
  13.000   1.3373   0.04708   0.03985  -0.0155   0.0428   1.0000
  13.250   1.3350   0.05022   0.04312  -0.0156   0.0402   1.0000
  13.500   1.3322   0.05344   0.04642  -0.0157   0.0386   1.0000
  13.750   1.3288   0.05679   0.04983  -0.0160   0.0372   1.0000
  14.000   1.3260   0.05990   0.05290  -0.0155   0.0357   1.0000
  14.250   1.3266   0.06298   0.05616  -0.0159   0.0345   1.0000
  14.500   1.3274   0.06603   0.05932  -0.0163   0.0333   1.0000
  14.750   1.3271   0.06930   0.06270  -0.0169   0.0320   1.0000
  15.000   1.3289   0.07225   0.06571  -0.0173   0.0311   1.0000
  15.250   1.3282   0.07562   0.06911  -0.0182   0.0301   1.0000
  15.500   1.3326   0.07803   0.07151  -0.0176   0.0290   1.0000
  15.750   1.3325   0.08154   0.07522  -0.0184   0.0285   1.0000
  16.000   1.3335   0.08492   0.07875  -0.0190   0.0280   1.0000
  16.250   1.3329   0.08860   0.08260  -0.0198   0.0274   1.0000
  16.500   1.3319   0.09240   0.08656  -0.0207   0.0269   1.0000
  16.750   1.3291   0.09657   0.09089  -0.0221   0.0265   1.0000
  17.000   1.3254   0.10098   0.09547  -0.0236   0.0262   1.0000
  17.250   1.3199   0.10576   0.10041  -0.0256   0.0258   1.0000
  17.500   1.3131   0.11085   0.10567  -0.0280   0.0256   1.0000
  17.750   1.3052   0.11625   0.11122  -0.0307   0.0252   1.0000
  18.000   1.2951   0.12223   0.11738  -0.0339   0.0251   1.0000
  18.250   1.2871   0.12779   0.12306  -0.0371   0.0248   1.0000
  18.500   1.2802   0.13320   0.12858  -0.0403   0.0244   1.0000
  18.750   1.2549   0.14320   0.13888  -0.0465   0.0248   1.0000
  19.000   1.1960   0.16260   0.15873  -0.0595   0.0264   1.0000
  19.250   1.1496   0.18060   0.17693  -0.0714   0.0277   1.0000
<< Back to GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)

Polar data table (+)

Polar graphs


<< Back to GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)