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GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il)
Reynolds number: 200,000
Max Cl/Cd: 73.88 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe329-il-200000.txt
Download as CSV file: xf-goe329-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 329 (PFALZ 58) 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  -0.2672   0.10367   0.10035  -0.0342   1.0000   0.0317
  -8.500  -0.2849   0.10346   0.10023  -0.0298   1.0000   0.0319
  -8.250  -0.3032   0.10325   0.10009  -0.0255   1.0000   0.0320
  -8.000  -0.2839   0.09919   0.09603  -0.0306   0.9959   0.0329
  -7.750  -0.2626   0.09495   0.09177  -0.0368   0.9904   0.0340
  -7.500  -0.2373   0.09069   0.08749  -0.0495   0.9809   0.0358
  -7.250  -0.2007   0.08484   0.08155  -0.0680   0.9721   0.0364
  -7.000  -0.1828   0.08018   0.07690  -0.0658   0.9707   0.0369
  -6.750  -0.1634   0.07658   0.07330  -0.0677   0.9644   0.0376
  -6.500  -0.1357   0.07257   0.06925  -0.0733   0.9598   0.0387
  -6.250  -0.1057   0.06845   0.06508  -0.0803   0.9549   0.0402
  -6.000  -0.0753   0.06451   0.06104  -0.0881   0.9463   0.0424
  -5.750  -0.0344   0.05917   0.05546  -0.0998   0.9395   0.0443
  -5.500  -0.0188   0.05624   0.05256  -0.0996   0.9316   0.0451
  -5.250   0.0064   0.05323   0.04950  -0.1019   0.9263   0.0464
  -5.000   0.0279   0.05060   0.04678  -0.1037   0.9163   0.0482
  -4.750   0.0781   0.04861   0.04415  -0.1114   0.9088   0.0529
  -4.500   0.0922   0.04402   0.03966  -0.1116   0.8998   0.0539
  -4.250   0.1112   0.04153   0.03718  -0.1116   0.8922   0.0551
  -4.000   0.1330   0.03950   0.03508  -0.1119   0.8830   0.0573
  -3.750   0.1716   0.03809   0.03306  -0.1144   0.8747   0.0646
  -3.500   0.1902   0.03487   0.02994  -0.1145   0.8659   0.0662
  -3.250   0.2127   0.03305   0.02808  -0.1145   0.8565   0.0687
  -2.750   0.2687   0.02941   0.02395  -0.1156   0.8378   0.0798
  -2.500   0.2939   0.02793   0.02239  -0.1156   0.8288   0.0846
  -2.250   0.3225   0.02636   0.02055  -0.1159   0.8184   0.0944
  -2.000   0.3506   0.02544   0.01936  -0.1161   0.8072   0.1079
  -1.750   0.3755   0.02387   0.01780  -0.1160   0.7965   0.1155
  -1.500   0.4028   0.02292   0.01662  -0.1162   0.7850   0.1402
  -1.250   0.4279   0.02166   0.01539  -0.1162   0.7717   0.1600
  -1.000   0.4535   0.02062   0.01429  -0.1163   0.7577   0.1915
  -0.250   0.4439   0.03683   0.03250  -0.1408   0.7160   0.1493
   0.000   0.5816   0.01669   0.00860  -0.1132   0.6934   0.0774
   0.250   0.6090   0.01549   0.00728  -0.1128   0.6738   0.0714
   0.500   0.6361   0.01500   0.00662  -0.1123   0.6517   0.0701
   0.750   0.6630   0.01464   0.00609  -0.1117   0.6305   0.0695
   1.000   0.6898   0.01437   0.00566  -0.1112   0.6097   0.0671
   1.250   0.7165   0.01421   0.00538  -0.1108   0.5902   0.0661
   1.500   0.7431   0.01410   0.00516  -0.1105   0.5726   0.0661
   1.750   0.7700   0.01402   0.00501  -0.1104   0.5565   0.0670
   2.000   0.7969   0.01404   0.00493  -0.1102   0.5418   0.0689
   2.250   0.8239   0.01414   0.00492  -0.1101   0.5288   0.0732
   2.500   0.8510   0.01428   0.00494  -0.1100   0.5176   0.0821
   2.750   0.8728   0.01299   0.00522  -0.1092   0.5076   0.7756
   3.000   0.8956   0.01287   0.00522  -0.1076   0.4978   1.0000
   3.250   0.9225   0.01323   0.00535  -0.1074   0.4890   1.0000
   3.500   0.9493   0.01349   0.00556  -0.1073   0.4796   1.0000
   3.750   0.9762   0.01385   0.00578  -0.1073   0.4721   1.0000
   4.000   1.0030   0.01413   0.00604  -0.1072   0.4642   1.0000
   4.250   1.0301   0.01453   0.00630  -0.1072   0.4579   1.0000
   4.500   1.0566   0.01480   0.00662  -0.1071   0.4506   1.0000
   4.750   1.0834   0.01515   0.00689  -0.1071   0.4443   1.0000
   5.000   1.1100   0.01551   0.00725  -0.1071   0.4382   1.0000
   5.250   1.1365   0.01584   0.00761  -0.1070   0.4324   1.0000
   5.500   1.1637   0.01626   0.00796  -0.1071   0.4275   1.0000
   5.750   1.1898   0.01662   0.00839  -0.1070   0.4221   1.0000
   6.000   1.2161   0.01697   0.00879  -0.1069   0.4167   1.0000
   6.250   1.2431   0.01740   0.00918  -0.1070   0.4122   1.0000
   6.500   1.2690   0.01782   0.00970  -0.1069   0.4076   1.0000
   6.750   1.2946   0.01819   0.01017  -0.1067   0.4025   1.0000
   7.000   1.3208   0.01856   0.01047  -0.1066   0.3963   1.0000
   7.250   1.3435   0.01876   0.01083  -0.1059   0.3877   1.0000
   7.500   1.3677   0.01902   0.01103  -0.1054   0.3791   1.0000
   7.750   1.3894   0.01916   0.01133  -0.1045   0.3698   1.0000
   8.000   1.4121   0.01942   0.01162  -0.1038   0.3614   1.0000
   8.250   1.4333   0.01958   0.01185  -0.1028   0.3517   1.0000
   8.500   1.4536   0.01979   0.01219  -0.1017   0.3414   1.0000
   8.750   1.4721   0.01996   0.01246  -0.1003   0.3285   1.0000
   9.000   1.4894   0.02016   0.01276  -0.0986   0.3134   1.0000
   9.250   1.5017   0.02047   0.01307  -0.0962   0.2871   1.0000
   9.500   1.5041   0.02143   0.01378  -0.0924   0.2218   1.0000
   9.750   1.4782   0.02442   0.01597  -0.0852   0.1139   1.0000
  10.000   1.4586   0.02756   0.01874  -0.0797   0.0634   1.0000
  10.250   1.4544   0.02979   0.02093  -0.0764   0.0486   1.0000
  10.500   1.4527   0.03197   0.02318  -0.0737   0.0436   1.0000
  10.750   1.4537   0.03404   0.02541  -0.0717   0.0409   1.0000
  11.000   1.4517   0.03649   0.02799  -0.0697   0.0389   1.0000
  11.250   1.4456   0.03947   0.03110  -0.0679   0.0374   1.0000
  11.500   1.4350   0.04309   0.03486  -0.0664   0.0363   1.0000
  11.750   1.4293   0.04641   0.03832  -0.0654   0.0354   1.0000
  12.000   1.4242   0.04981   0.04187  -0.0647   0.0345   1.0000
  12.250   1.4179   0.05348   0.04567  -0.0642   0.0335   1.0000
  12.500   1.4111   0.05734   0.04965  -0.0639   0.0328   1.0000
  12.750   1.4040   0.06131   0.05372  -0.0637   0.0321   1.0000
  13.000   1.3978   0.06525   0.05776  -0.0636   0.0315   1.0000
  13.250   1.3926   0.06905   0.06164  -0.0635   0.0310   1.0000
  13.500   1.3886   0.07260   0.06524  -0.0631   0.0304   1.0000
  13.750   1.3871   0.07560   0.06826  -0.0623   0.0298   1.0000
  14.000   1.3921   0.07711   0.06973  -0.0599   0.0291   1.0000
  14.250   1.3990   0.07909   0.07179  -0.0588   0.0287   1.0000
  14.500   1.4052   0.08132   0.07414  -0.0582   0.0281   1.0000
  14.750   1.4114   0.08355   0.07649  -0.0575   0.0274   1.0000
  15.000   1.4186   0.08562   0.07866  -0.0566   0.0267   1.0000
  15.250   1.4276   0.08739   0.08054  -0.0554   0.0262   1.0000
  15.500   1.4369   0.08921   0.08247  -0.0542   0.0259   1.0000
  15.750   1.4454   0.09123   0.08463  -0.0531   0.0256   1.0000
  16.000   1.4523   0.09361   0.08717  -0.0522   0.0254   1.0000
  16.250   1.4565   0.09651   0.09026  -0.0517   0.0254   1.0000
  16.500   1.4567   0.10011   0.09408  -0.0517   0.0254   1.0000
  16.750   1.4535   0.10424   0.09844  -0.0522   0.0254   1.0000
  17.000   1.4471   0.10889   0.10332  -0.0534   0.0255   1.0000
  17.250   1.4386   0.11397   0.10862  -0.0550   0.0254   1.0000
  17.500   1.4273   0.11964   0.11454  -0.0573   0.0255   1.0000
  17.750   1.4134   0.12599   0.12113  -0.0603   0.0257   1.0000
  18.000   1.3981   0.13282   0.12821  -0.0639   0.0259   1.0000
  18.250   1.3808   0.14033   0.13596  -0.0681   0.0262   1.0000
  18.500   1.3625   0.14833   0.14419  -0.0731   0.0265   1.0000
  18.750   1.3432   0.15703   0.15310  -0.0787   0.0270   1.0000
  19.000   1.3237   0.16617   0.16243  -0.0849   0.0275   1.0000
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