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GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.66 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe329-il-1000000.txt
Download as CSV file: xf-goe329-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1606   0.09716   0.09546  -0.0471   0.9143   0.0152
  -9.750  -0.1558   0.09432   0.09257  -0.0476   0.9023   0.0154
  -8.250  -0.2174   0.08887   0.08697  -0.0463   0.8825   0.0168
  -8.000  -0.2117   0.08528   0.08334  -0.0501   0.8708   0.0175
  -7.750  -0.2069   0.08151   0.07952  -0.0555   0.8601   0.0176
  -7.500  -0.1345   0.06262   0.06060  -0.0619   0.8291   0.0178
  -7.250  -0.1264   0.05935   0.05731  -0.0620   0.8226   0.0179
  -7.000  -0.1168   0.05625   0.05417  -0.0635   0.8161   0.0180
  -6.750  -0.1058   0.05299   0.05090  -0.0659   0.8099   0.0181
  -6.500  -0.0935   0.04962   0.04750  -0.0689   0.8033   0.0183
  -6.250  -0.0791   0.04627   0.04410  -0.0721   0.7973   0.0186
  -6.000  -0.0937   0.05726   0.05495  -0.0802   0.8091   0.0186
  -5.750  -0.0708   0.05421   0.05183  -0.0838   0.8022   0.0192
  -5.500  -0.0453   0.05081   0.04834  -0.0878   0.7959   0.0201
  -5.250  -0.0044   0.04547   0.04277  -0.0952   0.7893   0.0211
  -5.000   0.0241   0.04178   0.03892  -0.0982   0.7828   0.0212
  -4.750   0.0524   0.03823   0.03521  -0.1005   0.7756   0.0212
  -4.250   0.0982   0.03240   0.02917  -0.1037   0.7606   0.0218
  -4.000   0.1241   0.03062   0.02727  -0.1047   0.7526   0.0221
  -3.750   0.1515   0.02876   0.02531  -0.1058   0.7436   0.0225
  -3.500   0.1797   0.02683   0.02322  -0.1067   0.7341   0.0232
  -3.250   0.2131   0.02452   0.02061  -0.1072   0.7235   0.0251
  -3.000   0.2440   0.02272   0.01850  -0.1077   0.7123   0.0253
  -2.750   0.2731   0.02109   0.01659  -0.1081   0.7002   0.0253
  -2.500   0.3004   0.01794   0.01323  -0.1093   0.6868   0.0259
  -2.250   0.3282   0.01700   0.01215  -0.1098   0.6699   0.0263
  -2.000   0.3562   0.01621   0.01121  -0.1101   0.6497   0.0268
  -1.750   0.3845   0.01546   0.01025  -0.1104   0.6283   0.0278
  -1.500   0.4142   0.01554   0.01002  -0.1101   0.6053   0.0301
  -1.250   0.4428   0.01518   0.00938  -0.1102   0.5823   0.0302
  -1.000   0.4711   0.01311   0.00712  -0.1108   0.5608   0.0313
  -0.750   0.4990   0.01268   0.00656  -0.1111   0.5391   0.0320
  -0.500  -1.1691   0.01350   0.01030   0.2642   0.6123   0.0353
  -0.250   0.5554   0.01223   0.00582  -0.1113   0.5027   0.0350
   0.000   0.5840   0.01171   0.00509  -0.1114   0.4883   0.0375
   0.250   0.6121   0.01132   0.00468  -0.1116   0.4751   0.0388
   0.500   0.6404   0.01112   0.00443  -0.1118   0.4634   0.0408
   0.750   0.6686   0.01083   0.00406  -0.1120   0.4528   0.0463
   1.000   0.6965   0.01071   0.00391  -0.1121   0.4421   0.0499
   1.250   0.7260   0.01004   0.00311  -0.1119   0.4334   0.0337
   1.500   0.7543   0.00989   0.00291  -0.1121   0.4249   0.0329
   1.750   0.7827   0.00979   0.00279  -0.1123   0.4172   0.0328
   2.000   0.8109   0.00977   0.00273  -0.1124   0.4099   0.0334
   2.250   0.8394   0.00971   0.00265  -0.1126   0.4033   0.0332
   2.500   0.8674   0.00974   0.00263  -0.1128   0.3962   0.0335
   2.750   0.8958   0.00972   0.00262  -0.1130   0.3904   0.0343
   3.000   0.9238   0.00977   0.00264  -0.1131   0.3840   0.0356
   3.250   0.9517   0.00984   0.00269  -0.1132   0.3784   0.0366
   3.500   0.9798   0.00988   0.00272  -0.1133   0.3734   0.0389
   3.750   1.0074   0.00997   0.00280  -0.1134   0.3681   0.0439
   4.000   1.0283   0.00843   0.00314  -0.1125   0.3636   1.0000
   4.250   1.0563   0.00854   0.00324  -0.1127   0.3592   1.0000
   4.500   1.0838   0.00870   0.00335  -0.1128   0.3543   1.0000
   4.750   1.1108   0.00890   0.00351  -0.1128   0.3492   1.0000
   5.000   1.1387   0.00900   0.00363  -0.1129   0.3452   1.0000
   5.250   1.1659   0.00916   0.00376  -0.1130   0.3391   1.0000
   5.500   1.1928   0.00934   0.00391  -0.1130   0.3317   1.0000
   5.750   1.2200   0.00949   0.00406  -0.1130   0.3251   1.0000
   6.000   1.2464   0.00971   0.00424  -0.1130   0.3184   1.0000
   6.250   1.2735   0.00985   0.00438  -0.1130   0.3120   1.0000
   6.500   1.2997   0.01006   0.00457  -0.1129   0.3058   1.0000
   6.750   1.3264   0.01023   0.00475  -0.1129   0.2990   1.0000
   7.000   1.3520   0.01049   0.00497  -0.1128   0.2896   1.0000
   7.250   1.3780   0.01070   0.00516  -0.1127   0.2791   1.0000
   7.500   1.4028   0.01101   0.00542  -0.1124   0.2640   1.0000
   7.750   1.4257   0.01148   0.00576  -0.1118   0.2379   1.0000
   8.000   1.4308   0.01355   0.00710  -0.1086   0.1287   1.0000
   8.250   1.4297   0.01604   0.00894  -0.1044   0.0285   1.0000
   8.500   1.4486   0.01670   0.00958  -0.1032   0.0216   1.0000
   8.750   1.4670   0.01734   0.01024  -0.1018   0.0187   1.0000
   9.000   1.4865   0.01784   0.01078  -0.1007   0.0177   1.0000
   9.250   1.5046   0.01840   0.01138  -0.0993   0.0167   1.0000
   9.500   1.5202   0.01904   0.01205  -0.0976   0.0157   1.0000
   9.750   1.5293   0.01990   0.01299  -0.0947   0.0148   1.0000
  10.000   1.5413   0.02063   0.01378  -0.0924   0.0143   1.0000
  10.250   1.5543   0.02135   0.01455  -0.0904   0.0139   1.0000
  10.500   1.5662   0.02217   0.01542  -0.0884   0.0133   1.0000
  10.750   1.5768   0.02311   0.01642  -0.0864   0.0129   1.0000
  11.000   1.5862   0.02419   0.01757  -0.0844   0.0124   1.0000
  11.250   1.5929   0.02553   0.01897  -0.0823   0.0121   1.0000
  11.500   1.5942   0.02736   0.02090  -0.0799   0.0117   1.0000
  11.750   1.5902   0.02976   0.02343  -0.0773   0.0113   1.0000
  12.000   1.5978   0.03131   0.02505  -0.0760   0.0112   1.0000
  12.250   1.6031   0.03311   0.02693  -0.0747   0.0110   1.0000
  12.500   1.6066   0.03515   0.02907  -0.0734   0.0108   1.0000
  12.750   1.6086   0.03744   0.03145  -0.0722   0.0106   1.0000
  13.000   1.6090   0.03996   0.03406  -0.0712   0.0104   1.0000
  13.250   1.6083   0.04272   0.03690  -0.0703   0.0102   1.0000
  13.500   1.6076   0.04559   0.03986  -0.0697   0.0099   1.0000
  13.750   1.6047   0.04880   0.04316  -0.0692   0.0098   1.0000
  14.000   1.6017   0.05216   0.04661  -0.0689   0.0096   1.0000
  14.250   1.5968   0.05593   0.05047  -0.0689   0.0094   1.0000
  14.500   1.5899   0.06007   0.05470  -0.0691   0.0093   1.0000
  14.750   1.5809   0.06460   0.05933  -0.0694   0.0092   1.0000
  15.000   1.5699   0.06951   0.06434  -0.0700   0.0091   1.0000
  15.250   1.5567   0.07478   0.06972  -0.0706   0.0089   1.0000
  15.500   1.5419   0.08023   0.07527  -0.0713   0.0088   1.0000
  15.750   1.5251   0.08590   0.08105  -0.0719   0.0087   1.0000
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