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GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
Reynolds number: 200,000
Max Cl/Cd: 75.19 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe319-il-200000.txt
Download as CSV file: xf-goe319-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2299   0.10100   0.09757  -0.0299   1.0000   0.0404
  -8.500  -0.2273   0.09869   0.09533  -0.0309   1.0000   0.0412
  -8.250  -0.2394   0.09791   0.09467  -0.0292   1.0000   0.0417
  -8.000  -0.2252   0.09464   0.09139  -0.0470   0.9835   0.0424
  -7.750  -0.2034   0.08984   0.08662  -0.0436   0.9822   0.0428
  -7.500  -0.1792   0.08592   0.08270  -0.0458   0.9737   0.0436
  -7.250  -0.1559   0.08222   0.07899  -0.0506   0.9616   0.0446
  -7.000  -0.1340   0.07862   0.07536  -0.0559   0.9476   0.0458
  -6.750  -0.1148   0.07522   0.07192  -0.0614   0.9317   0.0473
  -6.500  -0.0864   0.07121   0.06767  -0.0780   0.9110   0.0488
  -6.250  -0.0778   0.06798   0.06448  -0.0749   0.8994   0.0492
  -6.000  -0.0668   0.06539   0.06186  -0.0731   0.8881   0.0497
  -5.750  -0.0527   0.06292   0.05936  -0.0733   0.8749   0.0505
  -5.500  -0.0355   0.06038   0.05675  -0.0747   0.8632   0.0517
  -5.250   0.0078   0.05776   0.05362  -0.0863   0.8520   0.0562
  -5.000   0.0186   0.05398   0.04995  -0.0850   0.8412   0.0567
  -4.750   0.0334   0.05146   0.04742  -0.0841   0.8319   0.0574
  -4.500   0.0520   0.04922   0.04512  -0.0842   0.8216   0.0585
  -4.250   0.0743   0.04700   0.04281  -0.0852   0.8119   0.0604
  -4.000   0.1133   0.04453   0.03982  -0.0899   0.8029   0.0652
  -3.750   0.1304   0.04179   0.03714  -0.0895   0.7935   0.0660
  -3.500   0.1508   0.03980   0.03509  -0.0893   0.7849   0.0674
  -3.250   0.1748   0.03804   0.03324  -0.0897   0.7751   0.0701
  -3.000   0.2080   0.03608   0.03080  -0.0912   0.7670   0.0759
  -2.750   0.2283   0.03407   0.02883  -0.0910   0.7566   0.0776
  -2.500   0.2524   0.03266   0.02728  -0.0908   0.7476   0.0814
  -2.250   0.2712   0.01501   0.00966  -0.0862   0.7188   0.0890
  -2.000   0.2936   0.01376   0.00832  -0.0859   0.7096   0.0919
  -1.750   0.3215   0.01280   0.00697  -0.0857   0.6988   0.1015
  -1.500   0.3439   0.01152   0.00570  -0.0856   0.6895   0.1041
  -1.250   0.3711   0.01091   0.00476  -0.0851   0.6803   0.1160
  -1.000   0.3944   0.00978   0.00366  -0.0851   0.6729   0.1199
  -0.750   0.4204   0.00912   0.00281  -0.0849   0.6644   0.1335
  -0.500   0.4459   0.00854   0.00207  -0.0845   0.6572   0.1494
  -0.250   0.4704   0.00792   0.00145  -0.0843   0.6487   0.1673
   0.000   0.5134   0.02097   0.01412  -0.0887   0.6521   0.1861
   0.250   0.5556   0.01795   0.00993  -0.0866   0.6455   0.0727
   0.500   0.5835   0.01700   0.00882  -0.0860   0.6378   0.0692
   0.750   0.6113   0.01628   0.00791  -0.0854   0.6290   0.0672
   1.000   0.6386   0.01576   0.00731  -0.0848   0.6207   0.0672
   1.250   0.6654   0.01540   0.00694  -0.0843   0.6112   0.0698
   1.500   0.6922   0.01508   0.00659  -0.0838   0.6018   0.0723
   1.750   0.7188   0.01475   0.00621  -0.0832   0.5924   0.0738
   2.000   0.7449   0.01441   0.00591  -0.0826   0.5822   0.0764
   2.250   0.7712   0.01420   0.00567  -0.0820   0.5729   0.0817
   2.500   0.7971   0.01401   0.00553  -0.0814   0.5613   0.0923
   2.750   0.8201   0.01302   0.00545  -0.0806   0.5506   0.4752
   3.000   0.8627   0.01215   0.00533  -0.0831   0.5369   1.0000
   3.250   0.8880   0.01231   0.00534  -0.0824   0.5230   1.0000
   3.500   0.9128   0.01247   0.00540  -0.0817   0.5073   1.0000
   3.750   0.9373   0.01266   0.00548  -0.0809   0.4902   1.0000
   4.000   0.9614   0.01288   0.00557  -0.0800   0.4714   1.0000
   4.250   0.9850   0.01310   0.00571  -0.0792   0.4484   1.0000
   4.500   1.0077   0.01341   0.00586  -0.0782   0.4233   1.0000
   4.750   1.0300   0.01379   0.00608  -0.0771   0.3977   1.0000
   5.000   1.0518   0.01426   0.00635  -0.0761   0.3760   1.0000
   5.250   1.0738   0.01476   0.00669  -0.0751   0.3589   1.0000
   5.500   1.0962   0.01525   0.00706  -0.0743   0.3444   1.0000
   5.750   1.1187   0.01574   0.00744  -0.0735   0.3325   1.0000
   6.000   1.1409   0.01631   0.00785  -0.0726   0.3229   1.0000
   6.250   1.1645   0.01672   0.00827  -0.0720   0.3143   1.0000
   6.500   1.1872   0.01732   0.00872  -0.0713   0.3073   1.0000
   6.750   1.2107   0.01773   0.00917  -0.0706   0.3005   1.0000
   7.000   1.2337   0.01823   0.00963  -0.0700   0.2943   1.0000
   7.250   1.2571   0.01881   0.01014  -0.0694   0.2888   1.0000
   7.500   1.2801   0.01925   0.01064  -0.0687   0.2834   1.0000
   7.750   1.3032   0.01976   0.01114  -0.0681   0.2784   1.0000
   8.000   1.3271   0.02045   0.01174  -0.0677   0.2737   1.0000
   8.250   1.3491   0.02090   0.01230  -0.0669   0.2691   1.0000
   8.500   1.3714   0.02141   0.01284  -0.0662   0.2642   1.0000
   8.750   1.3945   0.02206   0.01342  -0.0657   0.2594   1.0000
   9.000   1.4160   0.02266   0.01410  -0.0650   0.2548   1.0000
   9.250   1.4367   0.02319   0.01472  -0.0641   0.2501   1.0000
   9.500   1.4584   0.02378   0.01532  -0.0634   0.2457   1.0000
   9.750   1.4824   0.02462   0.01610  -0.0632   0.2412   1.0000
  10.000   1.5000   0.02517   0.01684  -0.0619   0.2369   1.0000
  10.250   1.5190   0.02576   0.01749  -0.0608   0.2321   1.0000
  10.500   1.5408   0.02648   0.01816  -0.0603   0.2275   1.0000
  10.750   1.5574   0.02723   0.01903  -0.0590   0.2227   1.0000
  11.000   1.5716   0.02781   0.01974  -0.0573   0.2177   1.0000
  11.250   1.5887   0.02842   0.02033  -0.0561   0.2129   1.0000
  11.500   1.6060   0.02930   0.02126  -0.0550   0.2084   1.0000
  11.750   1.6145   0.03001   0.02215  -0.0526   0.2043   1.0000
  12.000   1.6264   0.03072   0.02293  -0.0507   0.2002   1.0000
  12.250   1.6436   0.03149   0.02367  -0.0497   0.1964   1.0000
  12.500   1.6543   0.03251   0.02482  -0.0480   0.1927   1.0000
  12.750   1.6589   0.03349   0.02599  -0.0456   0.1889   1.0000
  13.000   1.6668   0.03438   0.02695  -0.0438   0.1850   1.0000
  13.250   1.6799   0.03521   0.02772  -0.0426   0.1811   1.0000
  13.500   1.6814   0.03657   0.02929  -0.0406   0.1774   1.0000
  13.750   1.6826   0.03795   0.03083  -0.0388   0.1734   1.0000
  14.000   1.6877   0.03918   0.03213  -0.0374   0.1697   1.0000
  14.250   1.6986   0.04031   0.03319  -0.0364   0.1660   1.0000
  14.500   1.6957   0.04236   0.03551  -0.0351   0.1627   1.0000
  14.750   1.6965   0.04423   0.03754  -0.0341   0.1589   1.0000
  15.000   1.6994   0.04598   0.03934  -0.0333   0.1555   1.0000
  15.250   1.7036   0.04777   0.04114  -0.0326   0.1518   1.0000
  15.500   1.6988   0.05048   0.04408  -0.0321   0.1482   1.0000
  15.750   1.6974   0.05292   0.04664  -0.0317   0.1446   1.0000
  16.000   1.6996   0.05500   0.04872  -0.0314   0.1412   1.0000
  16.250   1.6958   0.05791   0.05178  -0.0312   0.1378   1.0000
  16.500   1.6893   0.06129   0.05534  -0.0314   0.1341   1.0000
  16.750   1.6856   0.06439   0.05852  -0.0317   0.1306   1.0000
  17.000   1.6857   0.06702   0.06112  -0.0317   0.1269   1.0000
  17.250   1.6743   0.07144   0.06578  -0.0327   0.1236   1.0000
  17.500   1.6664   0.07548   0.06996  -0.0336   0.1201   1.0000
  17.750   1.6635   0.07877   0.07324  -0.0342   0.1167   1.0000
  18.000   1.6542   0.08313   0.07775  -0.0353   0.1136   1.0000
  18.250   1.6410   0.08830   0.08311  -0.0369   0.1104   1.0000
  18.500   1.6307   0.09305   0.08797  -0.0385   0.1072   1.0000
  18.750   1.6290   0.09625   0.09111  -0.0392   0.1037   1.0000
  19.000   1.6090   0.10289   0.09801  -0.0419   0.1011   1.0000
  19.250   1.5924   0.10903   0.10432  -0.0445   0.0981   1.0000
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