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GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.83 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe319-il-1000000-n5.txt
Download as CSV file: xf-goe319-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2463   0.09317   0.09054  -0.0292   0.7276   0.0155
  -8.500  -0.2397   0.08995   0.08729  -0.0310   0.7199   0.0157
  -8.250  -0.2434   0.08377   0.08108  -0.0356   0.7140   0.0164
  -8.000  -0.2329   0.08151   0.07882  -0.0370   0.7076   0.0165
  -7.750  -0.2223   0.07925   0.07654  -0.0388   0.7013   0.0166
  -7.500  -0.2102   0.07689   0.07416  -0.0412   0.6960   0.0167
  -7.250  -0.1953   0.07429   0.07156  -0.0443   0.6908   0.0169
  -7.000  -0.1793   0.07140   0.06865  -0.0479   0.6852   0.0172
  -6.750  -0.1625   0.06798   0.06518  -0.0522   0.6797   0.0174
  -6.500  -0.1438   0.06443   0.06160  -0.0567   0.6746   0.0176
  -6.250  -0.1235   0.06080   0.05792  -0.0612   0.6681   0.0177
  -6.000  -0.1018   0.05711   0.05415  -0.0656   0.6611   0.0179
  -5.750  -0.0784   0.05329   0.05026  -0.0699   0.6545   0.0181
  -5.500  -0.0538   0.04926   0.04613  -0.0741   0.6468   0.0184
  -5.250  -0.0251   0.04149   0.03811  -0.0810   0.6412   0.0193
  -5.000  -0.0003   0.03925   0.03577  -0.0825   0.6323   0.0194
  -4.750   0.0249   0.03715   0.03357  -0.0838   0.6224   0.0195
  -4.500   0.0505   0.03496   0.03125  -0.0849   0.6109   0.0197
  -4.250   0.0766   0.03250   0.02864  -0.0860   0.6012   0.0198
  -4.000   0.1029   0.02989   0.02586  -0.0869   0.5915   0.0199
  -3.750   0.1293   0.02750   0.02329  -0.0875   0.5809   0.0201
  -3.500   0.1557   0.02499   0.02057  -0.0879   0.5702   0.0205
  -3.250   0.1772   0.01481   0.00930  -0.0873   0.5641   0.0216
  -3.000   0.2029   0.01314   0.00724  -0.0869   0.5520   0.0218
  -2.750   0.2296   0.01245   0.00630  -0.0866   0.5368   0.0220
  -2.250   0.2841   0.01143   0.00496  -0.0860   0.5146   0.0224
  -2.000   0.3116   0.01102   0.00447  -0.0858   0.5072   0.0226
  -1.750   0.3394   0.01075   0.00414  -0.0856   0.5012   0.0228
  -1.500   0.3672   0.01053   0.00387  -0.0855   0.4944   0.0230
  -1.250   0.3949   0.01035   0.00363  -0.0853   0.4873   0.0232
  -1.000   0.4229   0.01016   0.00341  -0.0851   0.4809   0.0235
  -0.750   0.4507   0.01000   0.00320  -0.0849   0.4730   0.0238
  -0.500   0.4784   0.00985   0.00301  -0.0847   0.4657   0.0241
  -0.250   0.5061   0.00972   0.00284  -0.0845   0.4566   0.0244
   0.000   0.5337   0.00962   0.00269  -0.0843   0.4471   0.0247
   0.250   0.5611   0.00956   0.00257  -0.0841   0.4343   0.0250
   0.500   0.5883   0.00954   0.00247  -0.0838   0.4182   0.0252
   0.750   0.6154   0.00956   0.00241  -0.0836   0.3992   0.0255
   1.000   0.6422   0.00963   0.00239  -0.0833   0.3775   0.0257
   1.250   0.6684   0.00969   0.00234  -0.0829   0.3539   0.0264
   1.500   0.6948   0.00981   0.00237  -0.0826   0.3317   0.0270
   1.750   0.7212   0.00994   0.00242  -0.0823   0.3116   0.0276
   2.000   0.7478   0.01007   0.00247  -0.0820   0.2948   0.0281
   2.250   0.7745   0.01019   0.00253  -0.0817   0.2813   0.0287
   2.500   0.8012   0.01032   0.00260  -0.0815   0.2693   0.0293
   2.750   0.8283   0.01041   0.00266  -0.0813   0.2604   0.0299
   3.000   0.8550   0.01053   0.00274  -0.0810   0.2512   0.0311
   3.250   0.8820   0.01064   0.00283  -0.0808   0.2433   0.0324
   3.500   0.9085   0.01079   0.00294  -0.0806   0.2350   0.0343
   3.750   0.9356   0.01088   0.00303  -0.0804   0.2301   0.0383
   4.000   0.9624   0.01094   0.00318  -0.0802   0.2254   0.0871
   4.250   0.9887   0.01096   0.00337  -0.0800   0.2202   0.2030
   4.750   1.0481   0.00978   0.00382  -0.0814   0.2144   1.0000
   5.000   1.0743   0.00994   0.00395  -0.0811   0.2120   1.0000
   5.250   1.1004   0.01011   0.00410  -0.0807   0.2094   1.0000
   5.500   1.1262   0.01030   0.00426  -0.0804   0.2064   1.0000
   5.750   1.1518   0.01051   0.00444  -0.0800   0.2029   1.0000
   6.000   1.1778   0.01068   0.00460  -0.0797   0.2008   1.0000
   6.250   1.2039   0.01083   0.00476  -0.0794   0.1992   1.0000
   6.500   1.2298   0.01100   0.00493  -0.0791   0.1972   1.0000
   6.750   1.2555   0.01119   0.00512  -0.0788   0.1950   1.0000
   7.000   1.2809   0.01139   0.00531  -0.0785   0.1926   1.0000
   7.250   1.3059   0.01162   0.00552  -0.0781   0.1899   1.0000
   7.500   1.3307   0.01186   0.00576  -0.0777   0.1870   1.0000
   7.750   1.3559   0.01206   0.00597  -0.0773   0.1853   1.0000
   8.000   1.3811   0.01225   0.00618  -0.0770   0.1835   1.0000
   8.250   1.4059   0.01246   0.00640  -0.0766   0.1809   1.0000
   8.500   1.4300   0.01272   0.00665  -0.0761   0.1766   1.0000
   8.750   1.4533   0.01303   0.00693  -0.0756   0.1716   1.0000
   9.000   1.4775   0.01326   0.00718  -0.0751   0.1685   1.0000
   9.250   1.5010   0.01353   0.00745  -0.0746   0.1642   1.0000
   9.500   1.5233   0.01387   0.00777  -0.0739   0.1591   1.0000
   9.750   1.5458   0.01418   0.00808  -0.0733   0.1540   1.0000
  10.000   1.5664   0.01461   0.00846  -0.0724   0.1461   1.0000
  10.250   1.5865   0.01504   0.00886  -0.0714   0.1383   1.0000
  10.500   1.6049   0.01555   0.00934  -0.0702   0.1307   1.0000
  10.750   1.6229   0.01600   0.00978  -0.0689   0.1255   1.0000
  11.000   1.6383   0.01654   0.01031  -0.0672   0.1204   1.0000
  11.250   1.6553   0.01701   0.01079  -0.0658   0.1171   1.0000
  11.500   1.6713   0.01753   0.01134  -0.0644   0.1137   1.0000
  11.750   1.6854   0.01819   0.01200  -0.0628   0.1098   1.0000
  12.000   1.7002   0.01883   0.01267  -0.0614   0.1063   1.0000
  12.250   1.7144   0.01954   0.01339  -0.0600   0.1023   1.0000
  12.500   1.7267   0.02039   0.01425  -0.0585   0.0983   1.0000
  12.750   1.7398   0.02123   0.01511  -0.0572   0.0952   1.0000
  13.000   1.7533   0.02207   0.01599  -0.0560   0.0918   1.0000
  13.250   1.7629   0.02321   0.01713  -0.0546   0.0867   1.0000
  13.500   1.7730   0.02437   0.01831  -0.0534   0.0817   1.0000
  13.750   1.7793   0.02587   0.01979  -0.0520   0.0752   1.0000
  14.000   1.7846   0.02751   0.02143  -0.0507   0.0687   1.0000
  14.250   1.7894   0.02927   0.02320  -0.0495   0.0635   1.0000
  14.500   1.7916   0.03131   0.02524  -0.0484   0.0586   1.0000
  14.750   1.7952   0.03331   0.02728  -0.0474   0.0545   1.0000
  15.000   1.7958   0.03562   0.02962  -0.0465   0.0509   1.0000
  15.250   1.7988   0.03775   0.03179  -0.0458   0.0480   1.0000
  15.500   1.7973   0.04037   0.03446  -0.0451   0.0448   1.0000
  15.750   1.7964   0.04296   0.03710  -0.0445   0.0415   1.0000
  16.000   1.7914   0.04608   0.04026  -0.0439   0.0378   1.0000
  16.250   1.7845   0.04953   0.04374  -0.0436   0.0331   1.0000
  16.500   1.7661   0.05443   0.04866  -0.0435   0.0249   1.0000
  16.750   1.7483   0.05950   0.05378  -0.0437   0.0198   1.0000
  17.000   1.7353   0.06415   0.05850  -0.0441   0.0175   1.0000
  17.250   1.7256   0.06848   0.06292  -0.0447   0.0164   1.0000
  17.500   1.7149   0.07304   0.06757  -0.0454   0.0155   1.0000
  18.000   1.6919   0.08259   0.07733  -0.0472   0.0143   1.0000
  18.250   1.6797   0.08761   0.08245  -0.0483   0.0139   1.0000
  18.500   1.6658   0.09297   0.08793  -0.0497   0.0136   1.0000
  18.750   1.6500   0.09869   0.09376  -0.0513   0.0133   1.0000
  19.000   1.6330   0.10470   0.09989  -0.0531   0.0130   1.0000
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