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GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103.45 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe79-il-1000000-n5.txt
Download as CSV file: xf-goe79-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 79 (PFALZ 11) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3762   0.12190   0.12019  -0.0025   1.0000   0.0091
 -10.250  -0.3691   0.11873   0.11703  -0.0038   1.0000   0.0094
 -10.000  -0.3656   0.11429   0.11259  -0.0055   1.0000   0.0099
  -9.750  -0.3566   0.11189   0.11019  -0.0066   1.0000   0.0100
  -9.500  -0.3475   0.10948   0.10779  -0.0077   1.0000   0.0101
  -9.250  -0.3384   0.10707   0.10540  -0.0089   1.0000   0.0103
  -9.000  -0.3296   0.10456   0.10291  -0.0100   1.0000   0.0106
  -8.750  -0.3216   0.10186   0.10022  -0.0112   1.0000   0.0110
  -8.500  -0.3103   0.09863   0.09698  -0.0137   0.9756   0.0112
  -8.250  -0.2974   0.09376   0.09194  -0.0184   0.9036   0.0119
  -8.000  -0.2885   0.09168   0.08975  -0.0192   0.8779   0.0120
  -7.750  -0.2788   0.08952   0.08752  -0.0204   0.8593   0.0121
  -7.500  -0.2658   0.08700   0.08495  -0.0227   0.8431   0.0122
  -7.250  -0.2512   0.08433   0.08222  -0.0254   0.8277   0.0125
  -7.000  -0.2352   0.08161   0.07944  -0.0284   0.8128   0.0129
  -6.750  -0.2178   0.07848   0.07625  -0.0321   0.7971   0.0134
  -6.500  -0.1982   0.07480   0.07250  -0.0367   0.7797   0.0142
  -6.250  -0.1789   0.07253   0.07013  -0.0394   0.7577   0.0144
  -6.000  -0.1571   0.07013   0.06762  -0.0427   0.7324   0.0159
  -5.750  -0.1335   0.06688   0.06425  -0.0471   0.7079   0.0160
  -5.500  -0.1082   0.06361   0.06088  -0.0517   0.6865   0.0160
  -5.250  -0.0767   0.05974   0.05687  -0.0580   0.6680   0.0162
  -4.750  -0.0225   0.05366   0.05059  -0.0657   0.6364   0.0164
  -4.250   0.0317   0.04919   0.04597  -0.0714   0.6116   0.0169
  -4.000   0.0615   0.04688   0.04356  -0.0746   0.6001   0.0175
  -3.750   0.0972   0.04404   0.04059  -0.0787   0.5886   0.0185
  -3.500   0.1335   0.04111   0.03753  -0.0828   0.5791   0.0186
  -3.250   0.1696   0.03830   0.03456  -0.0864   0.5682   0.0187
  -3.000   0.2052   0.03567   0.03179  -0.0894   0.5582   0.0187
  -2.750   0.2392   0.03325   0.02922  -0.0918   0.5505   0.0187
  -2.500   0.2653   0.03132   0.02724  -0.0931   0.5419   0.0189
  -2.250   0.2930   0.02995   0.02579  -0.0943   0.5330   0.0191
  -2.000   0.3229   0.02856   0.02432  -0.0956   0.5247   0.0195
  -1.750   0.3543   0.02703   0.02267  -0.0969   0.5168   0.0201
  -1.500   0.3903   0.02523   0.02067  -0.0982   0.5045   0.0213
  -1.250   0.4244   0.02344   0.01867  -0.0993   0.4893   0.0214
  -1.000   0.4563   0.02191   0.01693  -0.1001   0.4717   0.0214
  -0.750   0.4875   0.02052   0.01536  -0.1008   0.4573   0.0214
  -0.500   0.5186   0.01929   0.01392  -0.1013   0.4386   0.0214
  -0.250   0.5485   0.01817   0.01256  -0.1019   0.4097   0.0214
   0.000   0.5763   0.01736   0.01154  -0.1026   0.3718   0.0211
   0.250   0.6056   0.01656   0.01050  -0.1030   0.3443   0.0208
   0.500   0.6360   0.01560   0.00930  -0.1032   0.3244   0.0208
   0.750   0.6666   0.01461   0.00806  -0.1033   0.3108   0.0211
   1.000   0.6966   0.01376   0.00699  -0.1033   0.3003   0.0213
   1.500   0.7540   0.01282   0.00580  -0.1035   0.2817   0.0219
   1.750   0.7832   0.01217   0.00497  -0.1035   0.2731   0.0218
   2.000   0.8116   0.01181   0.00450  -0.1034   0.2657   0.0218
   2.250   0.8397   0.01159   0.00423  -0.1034   0.2585   0.0220
   2.500   0.8676   0.01146   0.00403  -0.1034   0.2492   0.0223
   2.750   0.8955   0.01133   0.00384  -0.1033   0.2419   0.0227
   3.000   0.9233   0.01123   0.00368  -0.1032   0.2346   0.0233
   3.250   0.9513   0.01112   0.00354  -0.1032   0.2286   0.0237
   3.500   0.9789   0.01110   0.00347  -0.1031   0.2211   0.0243
   3.750   1.0066   0.01109   0.00344  -0.1030   0.2145   0.0249
   4.000   1.0341   0.01114   0.00344  -0.1030   0.2052   0.0252
   4.250   1.0616   0.01120   0.00349  -0.1029   0.1981   0.0257
   4.500   1.0888   0.01132   0.00357  -0.1028   0.1892   0.0264
   4.750   1.1160   0.01143   0.00367  -0.1027   0.1809   0.0272
   5.000   1.1428   0.01161   0.00380  -0.1025   0.1701   0.0278
   5.250   1.1692   0.01185   0.00397  -0.1023   0.1558   0.0290
   5.500   1.1924   0.01259   0.00443  -0.1017   0.1039   0.0302
   5.750   1.2176   0.01301   0.00477  -0.1014   0.0885   0.0313
   6.000   1.2436   0.01328   0.00502  -0.1011   0.0827   0.0325
   6.250   1.2699   0.01347   0.00522  -0.1008   0.0810   0.0348
   6.500   1.2962   0.01367   0.00545  -0.1006   0.0796   0.0407
   7.000   1.3449   0.01300   0.00621  -0.0997   0.0762   1.0000
   7.250   1.3703   0.01331   0.00651  -0.0994   0.0745   1.0000
   7.500   1.3956   0.01362   0.00683  -0.0990   0.0727   1.0000
   7.750   1.4206   0.01396   0.00718  -0.0986   0.0707   1.0000
   8.000   1.4460   0.01422   0.00746  -0.0982   0.0702   1.0000
   8.250   1.4713   0.01448   0.00776  -0.0979   0.0697   1.0000
   8.500   1.4964   0.01474   0.00805  -0.0975   0.0687   1.0000
   8.750   1.5212   0.01503   0.00835  -0.0971   0.0669   1.0000
   9.000   1.5455   0.01536   0.00870  -0.0967   0.0648   1.0000
   9.250   1.5693   0.01574   0.00908  -0.0962   0.0627   1.0000
   9.500   1.5926   0.01616   0.00951  -0.0956   0.0604   1.0000
   9.750   1.6166   0.01646   0.00984  -0.0951   0.0593   1.0000
  10.000   1.6404   0.01677   0.01019  -0.0946   0.0574   1.0000
  10.250   1.6634   0.01715   0.01057  -0.0940   0.0548   1.0000
  10.500   1.6855   0.01759   0.01100  -0.0933   0.0520   1.0000
  10.750   1.7077   0.01800   0.01144  -0.0926   0.0498   1.0000
  11.000   1.7292   0.01845   0.01190  -0.0918   0.0464   1.0000
  11.250   1.7495   0.01900   0.01242  -0.0909   0.0425   1.0000
  11.500   1.7690   0.01957   0.01300  -0.0898   0.0383   1.0000
  11.750   1.7873   0.02021   0.01364  -0.0886   0.0345   1.0000
  12.000   1.8037   0.02096   0.01439  -0.0872   0.0302   1.0000
  12.250   1.8186   0.02176   0.01519  -0.0855   0.0260   1.0000
  12.500   1.8310   0.02266   0.01610  -0.0835   0.0219   1.0000
  12.750   1.8404   0.02362   0.01708  -0.0810   0.0187   1.0000
  13.000   1.8455   0.02464   0.01814  -0.0779   0.0167   1.0000
  13.250   1.8516   0.02570   0.01926  -0.0752   0.0153   1.0000
  13.500   1.8566   0.02696   0.02058  -0.0726   0.0142   1.0000
  13.750   1.8623   0.02829   0.02199  -0.0705   0.0134   1.0000
  14.000   1.8680   0.02976   0.02354  -0.0688   0.0128   1.0000
  14.250   1.8723   0.03146   0.02532  -0.0672   0.0122   1.0000
  14.500   1.8750   0.03344   0.02738  -0.0659   0.0117   1.0000
  14.750   1.8762   0.03570   0.02972  -0.0648   0.0111   1.0000
  15.000   1.8769   0.03815   0.03227  -0.0640   0.0107   1.0000
  15.250   1.8782   0.04066   0.03488  -0.0634   0.0105   1.0000
  15.500   1.8776   0.04349   0.03781  -0.0630   0.0102   1.0000
  15.750   1.8754   0.04665   0.04107  -0.0629   0.0099   1.0000
  16.000   1.8711   0.05016   0.04470  -0.0630   0.0097   1.0000
  16.250   1.8643   0.05407   0.04871  -0.0633   0.0094   1.0000
  16.500   1.8553   0.05838   0.05313  -0.0639   0.0092   1.0000
  16.750   1.8442   0.06302   0.05789  -0.0645   0.0090   1.0000
  17.000   1.8311   0.06807   0.06306  -0.0655   0.0088   1.0000
  17.250   1.8163   0.07355   0.06866  -0.0667   0.0086   1.0000
  17.500   1.8000   0.07937   0.07460  -0.0682   0.0085   1.0000
  17.750   1.7822   0.08559   0.08095  -0.0699   0.0084   1.0000
  18.000   1.7630   0.09221   0.08771  -0.0720   0.0083   1.0000
  18.250   1.7450   0.09876   0.09438  -0.0742   0.0082   1.0000
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