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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 500,000
Max Cl/Cd: 102.15 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe123-il-500000-n5.txt
Download as CSV file: xf-goe123-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 123 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2765   0.09304   0.09078  -0.0358   0.9577   0.0094
  -8.000  -0.2710   0.08884   0.08656  -0.0384   0.9442   0.0097
  -7.750  -0.2620   0.08646   0.08416  -0.0397   0.9335   0.0099
  -7.500  -0.2507   0.08445   0.08214  -0.0412   0.9246   0.0102
  -7.250  -0.2373   0.08200   0.07967  -0.0435   0.9172   0.0108
  -7.000  -0.2226   0.07887   0.07650  -0.0469   0.9095   0.0114
  -6.750  -0.2067   0.07523   0.07283  -0.0511   0.9027   0.0117
  -6.500  -0.1879   0.07117   0.06873  -0.0561   0.8954   0.0121
  -6.250  -0.1649   0.06574   0.06322  -0.0633   0.8891   0.0128
  -6.000  -0.1443   0.06386   0.06133  -0.0656   0.8834   0.0131
  -5.750  -0.1218   0.06159   0.05901  -0.0686   0.8777   0.0140
  -5.500  -0.0959   0.05815   0.05550  -0.0732   0.8721   0.0149
  -5.250  -0.0659   0.05377   0.05103  -0.0792   0.8652   0.0156
  -5.000  -0.0344   0.04956   0.04669  -0.0849   0.8587   0.0166
  -4.750  -0.0104   0.04803   0.04512  -0.0865   0.8506   0.0173
  -4.250   0.0514   0.04195   0.03880  -0.0940   0.8377   0.0193
  -4.000   0.0924   0.03715   0.03377  -0.0998   0.8324   0.0211
  -3.750   0.1143   0.03646   0.03307  -0.1000   0.8270   0.0220
  -3.500   0.1430   0.03485   0.03138  -0.1017   0.8211   0.0241
  -3.250   0.1756   0.03196   0.02831  -0.1043   0.8156   0.0239
  -3.000   0.2081   0.02931   0.02550  -0.1064   0.8102   0.0241
  -2.750   0.2403   0.02684   0.02284  -0.1081   0.8035   0.0246
  -2.500   0.2728   0.02435   0.02011  -0.1095   0.7960   0.0253
  -2.250   0.3041   0.02190   0.01742  -0.1105   0.7859   0.0253
  -2.000   0.3349   0.01973   0.01498  -0.1112   0.7748   0.0256
  -1.750   0.3651   0.01761   0.01259  -0.1118   0.7647   0.0258
  -1.250   0.4246   0.01429   0.00868  -0.1125   0.7481   0.0264
  -1.000   0.4534   0.01300   0.00712  -0.1127   0.7400   0.0263
  -0.750   0.4819   0.01224   0.00615  -0.1128   0.7314   0.0264
  -0.500   0.5101   0.01143   0.00512  -0.1129   0.7221   0.0267
  -0.250   0.5382   0.01051   0.00402  -0.1129   0.7123   0.0273
   0.000   0.5660   0.01007   0.00348  -0.1129   0.7028   0.0279
   0.250   0.5936   0.00977   0.00311  -0.1128   0.6915   0.0283
   0.750   0.6483   0.00939   0.00259  -0.1126   0.6597   0.0293
   1.000   0.6751   0.00932   0.00243  -0.1123   0.6350   0.0303
   1.250   0.7014   0.00931   0.00228  -0.1120   0.6026   0.0308
   1.500   0.7271   0.00940   0.00217  -0.1116   0.5622   0.0309
   1.750   0.7530   0.00951   0.00212  -0.1113   0.5292   0.0311
   2.000   0.7793   0.00962   0.00211  -0.1111   0.5030   0.0315
   2.250   0.8057   0.00974   0.00214  -0.1108   0.4799   0.0320
   2.500   0.8324   0.00984   0.00217  -0.1107   0.4601   0.0329
   2.750   0.8588   0.01000   0.00223  -0.1105   0.4372   0.0339
   3.000   0.8847   0.01022   0.00233  -0.1102   0.4086   0.0349
   3.250   0.9105   0.01045   0.00245  -0.1099   0.3833   0.0370
   3.500   0.9366   0.01066   0.00259  -0.1097   0.3624   0.0420
   3.750   0.9628   0.01080   0.00280  -0.1095   0.3456   0.0946
   4.000   0.9889   0.01099   0.00302  -0.1093   0.3317   0.1314
   4.250   1.0147   0.01121   0.00322  -0.1091   0.3161   0.1497
   4.500   1.0401   0.01147   0.00344  -0.1088   0.2977   0.1705
   5.000   1.0869   0.01064   0.00397  -0.1075   0.2734   1.0000
   5.250   1.1126   0.01090   0.00420  -0.1072   0.2623   1.0000
   5.500   1.1379   0.01119   0.00444  -0.1069   0.2490   1.0000
   5.750   1.1627   0.01155   0.00473  -0.1065   0.2286   1.0000
   6.000   1.1862   0.01203   0.00506  -0.1060   0.1998   1.0000
   6.250   1.2091   0.01257   0.00545  -0.1054   0.1716   1.0000
   6.500   1.2318   0.01314   0.00588  -0.1047   0.1456   1.0000
   6.750   1.2504   0.01416   0.00657  -0.1036   0.0900   1.0000
   7.000   1.2728   0.01473   0.00709  -0.1028   0.0752   1.0000
   7.250   1.2934   0.01548   0.00770  -0.1019   0.0454   1.0000
   7.500   1.3134   0.01627   0.00838  -0.1009   0.0304   1.0000
   7.750   1.3357   0.01678   0.00893  -0.1001   0.0255   1.0000
   8.000   1.3570   0.01736   0.00955  -0.0992   0.0210   1.0000
   8.250   1.3781   0.01794   0.01017  -0.0983   0.0178   1.0000
   8.500   1.3990   0.01851   0.01078  -0.0974   0.0155   1.0000
   8.750   1.4182   0.01923   0.01152  -0.0962   0.0136   1.0000
   9.000   1.4374   0.01991   0.01229  -0.0950   0.0125   1.0000
   9.250   1.4562   0.02056   0.01301  -0.0938   0.0115   1.0000
   9.500   1.4742   0.02124   0.01375  -0.0925   0.0105   1.0000
   9.750   1.4899   0.02208   0.01464  -0.0909   0.0096   1.0000
  10.000   1.5020   0.02310   0.01574  -0.0887   0.0090   1.0000
  10.250   1.5143   0.02392   0.01666  -0.0865   0.0086   1.0000
  10.500   1.5252   0.02486   0.01772  -0.0842   0.0082   1.0000
  10.750   1.5350   0.02590   0.01886  -0.0819   0.0079   1.0000
  11.000   1.5441   0.02703   0.02008  -0.0797   0.0075   1.0000
  11.250   1.5527   0.02822   0.02136  -0.0776   0.0072   1.0000
  11.500   1.5606   0.02950   0.02273  -0.0756   0.0069   1.0000
  11.750   1.5657   0.03107   0.02438  -0.0735   0.0066   1.0000
  12.000   1.5645   0.03325   0.02668  -0.0710   0.0063   1.0000
  12.250   1.5707   0.03485   0.02839  -0.0694   0.0061   1.0000
  12.500   1.5749   0.03670   0.03038  -0.0677   0.0059   1.0000
  12.750   1.5771   0.03881   0.03263  -0.0661   0.0058   1.0000
  13.000   1.5777   0.04115   0.03510  -0.0647   0.0056   1.0000
  13.250   1.5776   0.04369   0.03777  -0.0634   0.0055   1.0000
  13.500   1.5764   0.04641   0.04062  -0.0624   0.0053   1.0000
  13.750   1.5742   0.04936   0.04370  -0.0615   0.0052   1.0000
  14.000   1.5712   0.05252   0.04700  -0.0609   0.0051   1.0000
  14.250   1.5673   0.05590   0.05051  -0.0605   0.0050   1.0000
  14.500   1.5625   0.05953   0.05427  -0.0604   0.0049   1.0000
  14.750   1.5568   0.06349   0.05837  -0.0607   0.0048   1.0000
  15.000   1.5505   0.06767   0.06269  -0.0612   0.0048   1.0000
  15.250   1.5434   0.07217   0.06733  -0.0620   0.0047   1.0000
  15.500   1.5353   0.07699   0.07229  -0.0631   0.0046   1.0000
  15.750   1.5261   0.08211   0.07755  -0.0645   0.0046   1.0000
  16.000   1.5161   0.08749   0.08305  -0.0661   0.0045   1.0000
  16.250   1.5053   0.09312   0.08882  -0.0680   0.0045   1.0000
  16.500   1.4938   0.09899   0.09483  -0.0700   0.0045   1.0000
  16.750   1.4818   0.10504   0.10101  -0.0723   0.0044   1.0000
  17.000   1.4694   0.11124   0.10735  -0.0747   0.0044   1.0000
  17.250   1.4567   0.11763   0.11387  -0.0774   0.0043   1.0000
  17.500   1.4443   0.12411   0.12047  -0.0802   0.0043   1.0000
  17.750   1.4318   0.13069   0.12719  -0.0833   0.0043   1.0000
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