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

GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
Reynolds number: 500,000
Max Cl/Cd: 91.06 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe319-il-500000-n5.txt
Download as CSV file: xf-goe319-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2452   0.10094   0.09826  -0.0299   0.8553   0.0222
  -9.000  -0.2406   0.09778   0.09504  -0.0318   0.8371   0.0222
  -8.750  -0.2359   0.09459   0.09178  -0.0338   0.8183   0.0222
  -8.500  -0.2311   0.09132   0.08844  -0.0362   0.8004   0.0223
  -8.250  -0.2230   0.08830   0.08536  -0.0372   0.7851   0.0223
  -8.000  -0.2121   0.08589   0.08289  -0.0371   0.7719   0.0225
  -7.750  -0.2018   0.08354   0.08050  -0.0379   0.7604   0.0226
  -7.500  -0.1919   0.08116   0.07807  -0.0393   0.7499   0.0229
  -7.250  -0.1818   0.07867   0.07555  -0.0413   0.7403   0.0233
  -7.000  -0.1685   0.07580   0.07263  -0.0445   0.7320   0.0238
  -6.750  -0.1535   0.07257   0.06937  -0.0484   0.7242   0.0245
  -6.500  -0.1330   0.06787   0.06457  -0.0566   0.7173   0.0255
  -6.250  -0.1104   0.06319   0.05980  -0.0638   0.7113   0.0257
  -6.000  -0.0877   0.05906   0.05558  -0.0687   0.7051   0.0257
  -5.750  -0.0636   0.05489   0.05128  -0.0732   0.6991   0.0258
  -5.500  -0.0451   0.05201   0.04835  -0.0748   0.6932   0.0260
  -5.250  -0.0252   0.04999   0.04630  -0.0757   0.6864   0.0262
  -5.000  -0.0031   0.04776   0.04399  -0.0772   0.6797   0.0264
  -4.750   0.0208   0.04538   0.04154  -0.0790   0.6725   0.0267
  -4.500   0.0457   0.04296   0.03902  -0.0807   0.6648   0.0271
  -4.250   0.0717   0.04045   0.03638  -0.0825   0.6573   0.0277
  -4.000   0.1069   0.03578   0.03138  -0.0856   0.6493   0.0296
  -3.500   0.1574   0.02817   0.02328  -0.0874   0.6325   0.0256
  -3.250   0.1829   0.02604   0.02095  -0.0877   0.6232   0.0255
  -3.000   0.2092   0.02310   0.01772  -0.0877   0.6136   0.0254
  -2.750   0.2352   0.01969   0.01388  -0.0875   0.6046   0.0255
  -2.500   0.2611   0.01723   0.01096  -0.0870   0.5940   0.0256
  -2.250   0.2874   0.01582   0.00921  -0.0867   0.5813   0.0260
  -2.000   0.3139   0.01515   0.00836  -0.0864   0.5675   0.0263
  -1.750   0.3407   0.01441   0.00741  -0.0860   0.5557   0.0264
  -1.500   0.3680   0.01379   0.00663  -0.0858   0.5463   0.0266
  -1.250   0.3952   0.01330   0.00600  -0.0855   0.5376   0.0268
  -1.000   0.4226   0.01288   0.00546  -0.0852   0.5289   0.0271
  -0.750   0.4499   0.01252   0.00500  -0.0849   0.5214   0.0274
  -0.500   0.4775   0.01219   0.00458  -0.0847   0.5139   0.0278
  -0.250   0.5048   0.01193   0.00423  -0.0844   0.5061   0.0281
   0.000   0.5323   0.01168   0.00393  -0.0841   0.4987   0.0285
   0.250   0.5596   0.01149   0.00368  -0.0838   0.4903   0.0289
   0.500   0.5869   0.01135   0.00349  -0.0836   0.4823   0.0294
   0.750   0.6141   0.01122   0.00332  -0.0833   0.4729   0.0300
   1.000   0.6411   0.01106   0.00317  -0.0830   0.4632   0.0307
   1.250   0.6679   0.01100   0.00307  -0.0827   0.4511   0.0312
   1.500   0.6947   0.01097   0.00300  -0.0824   0.4365   0.0318
   1.750   0.7214   0.01098   0.00295  -0.0821   0.4200   0.0325
   2.000   0.7478   0.01104   0.00294  -0.0817   0.4010   0.0333
   2.250   0.7738   0.01116   0.00296  -0.0814   0.3786   0.0340
   2.500   0.7993   0.01133   0.00302  -0.0809   0.3548   0.0351
   2.750   0.8248   0.01153   0.00312  -0.0805   0.3331   0.0370
   3.000   0.8504   0.01174   0.00324  -0.0801   0.3143   0.0393
   3.250   0.8761   0.01193   0.00337  -0.0797   0.2991   0.0426
   3.500   0.9017   0.01212   0.00353  -0.0793   0.2858   0.0582
   3.750   0.9272   0.01213   0.00377  -0.0790   0.2745   0.1881
   4.250   0.9859   0.01109   0.00427  -0.0803   0.2568   1.0000
   4.750   1.0360   0.01160   0.00465  -0.0793   0.2419   1.0000
   5.250   1.0862   0.01210   0.00506  -0.0783   0.2320   1.0000
   5.500   1.1115   0.01232   0.00525  -0.0779   0.2286   1.0000
   5.750   1.1365   0.01256   0.00547  -0.0775   0.2252   1.0000
   6.000   1.1610   0.01283   0.00572  -0.0769   0.2219   1.0000
   6.250   1.1852   0.01312   0.00598  -0.0764   0.2185   1.0000
   6.500   1.2102   0.01334   0.00621  -0.0760   0.2164   1.0000
   6.750   1.2350   0.01357   0.00646  -0.0755   0.2137   1.0000
   7.000   1.2593   0.01383   0.00672  -0.0750   0.2106   1.0000
   7.250   1.2831   0.01412   0.00700  -0.0744   0.2075   1.0000
   7.500   1.3063   0.01444   0.00731  -0.0738   0.2046   1.0000
   7.750   1.3290   0.01479   0.00766  -0.0731   0.2017   1.0000
   8.000   1.3530   0.01503   0.00794  -0.0726   0.1999   1.0000
   8.250   1.3765   0.01530   0.00825  -0.0720   0.1976   1.0000
   8.500   1.3994   0.01559   0.00857  -0.0714   0.1949   1.0000
   8.750   1.4217   0.01592   0.00892  -0.0706   0.1921   1.0000
   9.000   1.4430   0.01629   0.00929  -0.0698   0.1893   1.0000
   9.250   1.4631   0.01672   0.00973  -0.0688   0.1861   1.0000
   9.500   1.4854   0.01700   0.01006  -0.0681   0.1830   1.0000
   9.750   1.5058   0.01734   0.01043  -0.0671   0.1785   1.0000
  10.000   1.5236   0.01777   0.01087  -0.0658   0.1742   1.0000
  10.250   1.5410   0.01823   0.01135  -0.0644   0.1707   1.0000
  10.500   1.5597   0.01864   0.01181  -0.0633   0.1669   1.0000
  10.750   1.5767   0.01914   0.01233  -0.0620   0.1622   1.0000
  11.000   1.5918   0.01977   0.01296  -0.0606   0.1574   1.0000
  11.250   1.6083   0.02035   0.01357  -0.0594   0.1519   1.0000
  11.750   1.6358   0.02190   0.01514  -0.0567   0.1398   1.0000
  12.000   1.6481   0.02281   0.01606  -0.0553   0.1345   1.0000
  12.250   1.6603   0.02378   0.01705  -0.0541   0.1304   1.0000
  12.500   1.6725   0.02477   0.01809  -0.0529   0.1263   1.0000
  12.750   1.6826   0.02596   0.01931  -0.0517   0.1221   1.0000
  13.000   1.6923   0.02722   0.02060  -0.0506   0.1185   1.0000
  13.250   1.7027   0.02847   0.02191  -0.0496   0.1147   1.0000
  13.500   1.7107   0.02996   0.02344  -0.0486   0.1108   1.0000
  13.750   1.7168   0.03166   0.02517  -0.0476   0.1072   1.0000
  14.000   1.7260   0.03312   0.02671  -0.0469   0.1041   1.0000
  14.250   1.7327   0.03485   0.02850  -0.0461   0.1005   1.0000
  14.500   1.7367   0.03686   0.03055  -0.0453   0.0973   1.0000
  14.750   1.7419   0.03879   0.03255  -0.0447   0.0945   1.0000
  15.000   1.7469   0.04077   0.03461  -0.0441   0.0907   1.0000
  15.250   1.7469   0.04327   0.03714  -0.0435   0.0862   1.0000
  15.500   1.7481   0.04569   0.03962  -0.0430   0.0817   1.0000
  15.750   1.7460   0.04855   0.04253  -0.0426   0.0767   1.0000
  16.000   1.7437   0.05152   0.04555  -0.0424   0.0724   1.0000
  16.250   1.7386   0.05489   0.04896  -0.0423   0.0680   1.0000
  16.500   1.7332   0.05840   0.05254  -0.0424   0.0645   1.0000
  16.750   1.7266   0.06214   0.05635  -0.0426   0.0611   1.0000
  17.000   1.7175   0.06629   0.06056  -0.0430   0.0582   1.0000
  17.250   1.7088   0.07048   0.06483  -0.0435   0.0551   1.0000
  17.500   1.6964   0.07527   0.06971  -0.0444   0.0522   1.0000
  17.750   1.6845   0.08006   0.07459  -0.0453   0.0499   1.0000
  18.000   1.6729   0.08491   0.07954  -0.0463   0.0476   1.0000
  18.250   1.6574   0.09044   0.08517  -0.0477   0.0454   1.0000
  18.500   1.6416   0.09610   0.09093  -0.0492   0.0435   1.0000
  18.750   1.6260   0.10182   0.09676  -0.0509   0.0410   1.0000
  19.000   1.6063   0.10835   0.10339  -0.0530   0.0386   1.0000
  19.250   1.5876   0.11482   0.10996  -0.0553   0.0363   1.0000
<< Back to GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)

Polar data table (+)

Polar graphs


<< Back to GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)