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GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)
Reynolds number: 200,000
Max Cl/Cd: 71.25 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe314-il-200000-n5.txt
Download as CSV file: xf-goe314-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3090   0.09148   0.08798  -0.0242   1.0000   0.0318
  -7.750  -0.3079   0.08918   0.08573  -0.0238   1.0000   0.0322
  -7.500  -0.3100   0.08707   0.08368  -0.0231   1.0000   0.0326
  -7.250  -0.3143   0.08513   0.08181  -0.0221   1.0000   0.0332
  -7.000  -0.3156   0.08293   0.07967  -0.0220   1.0000   0.0343
  -6.750  -0.2891   0.07850   0.07518  -0.0354   0.9899   0.0366
  -6.500  -0.2583   0.07356   0.07013  -0.0453   0.9779   0.0368
  -6.250  -0.2301   0.06897   0.06540  -0.0520   0.9659   0.0369
  -6.000  -0.2150   0.06485   0.06134  -0.0520   0.9569   0.0374
  -5.750  -0.1933   0.06179   0.05829  -0.0533   0.9478   0.0382
  -5.500  -0.1661   0.05869   0.05514  -0.0569   0.9356   0.0396
  -5.250  -0.1335   0.05508   0.05141  -0.0623   0.9228   0.0415
  -5.000  -0.0850   0.05109   0.04703  -0.0715   0.9086   0.0441
  -4.750  -0.0491   0.04758   0.04322  -0.0758   0.8945   0.0443
  -4.250   0.0001   0.04098   0.03651  -0.0794   0.8642   0.0457
  -4.000   0.0253   0.03880   0.03419  -0.0805   0.8478   0.0466
  -3.750   0.0505   0.03665   0.03186  -0.0812   0.8317   0.0475
  -3.500   0.0755   0.03461   0.02961  -0.0816   0.8160   0.0486
  -3.250   0.1083   0.03156   0.02588  -0.0817   0.8016   0.0442
  -3.000   0.1273   0.02952   0.02386  -0.0815   0.7854   0.0428
  -2.750   0.1517   0.02768   0.02177  -0.0810   0.7693   0.0426
  -2.500   0.1766   0.02594   0.01974  -0.0804   0.7523   0.0430
  -2.250   0.2005   0.02431   0.01787  -0.0798   0.7341   0.0420
  -2.000   0.2251   0.02272   0.01599  -0.0790   0.7146   0.0412
  -1.750   0.2499   0.02125   0.01419  -0.0781   0.6937   0.0406
  -1.500   0.2749   0.01994   0.01256  -0.0772   0.6706   0.0405
  -1.250   0.2998   0.01882   0.01111  -0.0762   0.6463   0.0406
  -1.000   0.3247   0.01790   0.00987  -0.0753   0.6213   0.0410
  -0.500   0.3748   0.01660   0.00794  -0.0734   0.5727   0.0434
  -0.250   0.3999   0.01603   0.00710  -0.0726   0.5521   0.0437
   0.000   0.4251   0.01558   0.00641  -0.0718   0.5337   0.0441
   0.250   0.4503   0.01515   0.00581  -0.0711   0.5173   0.0446
   0.500   0.4754   0.01472   0.00530  -0.0704   0.5027   0.0455
   0.750   0.5006   0.01446   0.00497  -0.0698   0.4894   0.0465
   1.000   0.5258   0.01430   0.00476  -0.0692   0.4770   0.0483
   1.250   0.5509   0.01421   0.00458  -0.0685   0.4645   0.0509
   1.500   0.5756   0.01411   0.00438  -0.0678   0.4510   0.0525
   1.750   0.6003   0.01393   0.00417  -0.0671   0.4379   0.0539
   2.000   0.6250   0.01378   0.00402  -0.0664   0.4265   0.0561
   2.250   0.6498   0.01375   0.00396  -0.0657   0.4174   0.0587
   2.500   0.6753   0.01375   0.00393  -0.0652   0.4086   0.0631
   2.750   0.7003   0.01376   0.00393  -0.0646   0.4011   0.0694
   3.250   0.7509   0.01386   0.00404  -0.0635   0.3853   0.0905
   3.500   0.7702   0.01275   0.00421  -0.0621   0.3775   0.6665
   4.000   0.8493   0.01270   0.00449  -0.0669   0.3552   1.0000
   4.250   0.8733   0.01289   0.00464  -0.0661   0.3433   1.0000
   4.500   0.8971   0.01311   0.00479  -0.0653   0.3319   1.0000
   4.750   0.9206   0.01335   0.00496  -0.0644   0.3215   1.0000
   5.000   0.9444   0.01357   0.00516  -0.0636   0.3113   1.0000
   5.250   0.9682   0.01381   0.00539  -0.0629   0.3022   1.0000
   5.500   0.9915   0.01409   0.00561  -0.0620   0.2930   1.0000
   5.750   1.0153   0.01433   0.00587  -0.0613   0.2838   1.0000
   6.000   1.0384   0.01462   0.00614  -0.0604   0.2750   1.0000
   6.250   1.0616   0.01491   0.00643  -0.0596   0.2655   1.0000
   6.500   1.0845   0.01522   0.00673  -0.0588   0.2559   1.0000
   6.750   1.1068   0.01556   0.00706  -0.0579   0.2464   1.0000
   7.000   1.1290   0.01591   0.00740  -0.0570   0.2347   1.0000
   7.250   1.1512   0.01627   0.00776  -0.0561   0.2248   1.0000
   7.500   1.1728   0.01666   0.00815  -0.0551   0.2170   1.0000
   7.750   1.1951   0.01701   0.00856  -0.0542   0.2097   1.0000
   8.000   1.2161   0.01744   0.00900  -0.0532   0.2031   1.0000
   8.250   1.2380   0.01780   0.00943  -0.0523   0.1966   1.0000
   8.500   1.2582   0.01827   0.00991  -0.0511   0.1891   1.0000
   8.750   1.2790   0.01869   0.01041  -0.0501   0.1804   1.0000
   9.000   1.2980   0.01921   0.01094  -0.0489   0.1697   1.0000
   9.250   1.3160   0.01980   0.01151  -0.0475   0.1555   1.0000
   9.500   1.3334   0.02042   0.01213  -0.0461   0.1384   1.0000
   9.750   1.3421   0.02165   0.01306  -0.0437   0.0871   1.0000
  10.000   1.3480   0.02304   0.01430  -0.0409   0.0698   1.0000
  10.250   1.3554   0.02412   0.01540  -0.0382   0.0636   1.0000
  10.500   1.3647   0.02502   0.01638  -0.0357   0.0596   1.0000
  10.750   1.3734   0.02595   0.01744  -0.0333   0.0564   1.0000
  11.000   1.3793   0.02709   0.01867  -0.0307   0.0534   1.0000
  11.250   1.3827   0.02843   0.02010  -0.0282   0.0502   1.0000
  11.500   1.3925   0.02940   0.02124  -0.0264   0.0469   1.0000
  11.750   1.3972   0.03077   0.02273  -0.0245   0.0429   1.0000
  12.000   1.4015   0.03225   0.02432  -0.0228   0.0393   1.0000
  12.250   1.4068   0.03376   0.02594  -0.0214   0.0348   1.0000
  12.500   1.4098   0.03557   0.02784  -0.0201   0.0297   1.0000
  12.750   1.4094   0.03779   0.03012  -0.0191   0.0258   1.0000
  13.000   1.4069   0.04038   0.03277  -0.0184   0.0235   1.0000
  13.250   1.4017   0.04347   0.03595  -0.0181   0.0219   1.0000
  13.500   1.3952   0.04694   0.03956  -0.0183   0.0208   1.0000
  13.750   1.3865   0.05094   0.04368  -0.0189   0.0199   1.0000
  14.000   1.3762   0.05543   0.04829  -0.0200   0.0192   1.0000
  14.250   1.3653   0.06022   0.05322  -0.0215   0.0188   1.0000
  14.500   1.3509   0.06572   0.05884  -0.0233   0.0183   1.0000
  15.000   1.3253   0.07661   0.07000  -0.0272   0.0178   1.0000
  15.250   1.3134   0.08209   0.07562  -0.0293   0.0176   1.0000
  15.500   1.3022   0.08755   0.08121  -0.0314   0.0174   1.0000
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