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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 100,000
Max Cl/Cd: 34.28 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe54-il-100000.txt
Download as CSV file: xf-goe54-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 54 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5667   0.11954   0.11472   0.0417   1.0000   0.0433
  -8.750  -0.5648   0.11711   0.11234   0.0378   1.0000   0.0438
  -8.500  -0.5646   0.11488   0.11017   0.0326   1.0000   0.0440
  -8.250  -0.5577   0.11054   0.10588   0.0313   1.0000   0.0443
  -8.000  -0.5452   0.10539   0.10073   0.0343   1.0000   0.0452
  -7.750  -0.5376   0.10175   0.09713   0.0336   1.0000   0.0463
  -7.500  -0.5304   0.09834   0.09376   0.0316   1.0000   0.0476
  -7.250  -0.5203   0.09474   0.09019   0.0278   1.0000   0.0492
  -7.000  -0.5046   0.09114   0.08657   0.0191   1.0000   0.0508
  -6.750  -0.4802   0.08743   0.08271   0.0061   1.0000   0.0515
  -6.500  -0.4748   0.08252   0.07793   0.0110   1.0000   0.0523
  -6.250  -0.4624   0.07868   0.07414   0.0110   1.0000   0.0536
  -6.000  -0.4453   0.07493   0.07037   0.0083   1.0000   0.0554
  -5.750  -0.4222   0.07113   0.06650   0.0033   1.0000   0.0580
  -5.500  -0.3898   0.06714   0.06226  -0.0051   1.0000   0.0606
  -5.250  -0.3783   0.06316   0.05841  -0.0037   1.0000   0.0625
  -5.000  -0.3561   0.05984   0.05504  -0.0059   1.0000   0.0663
  -4.750  -0.3195   0.05662   0.05146  -0.0121   1.0000   0.0710
  -4.500  -0.3037   0.05275   0.04773  -0.0119   1.0000   0.0734
  -4.250  -0.2768   0.04996   0.04484  -0.0139   1.0000   0.0793
  -4.000  -0.2480   0.04667   0.04138  -0.0165   1.0000   0.0846
  -3.750  -0.2194   0.04463   0.03919  -0.0181   1.0000   0.0939
  -3.500  -0.1959   0.04109   0.03569  -0.0193   1.0000   0.1002
  -3.250  -0.1675   0.03860   0.03309  -0.0209   1.0000   0.1131
  -3.000  -0.1398   0.03617   0.03062  -0.0223   1.0000   0.1278
  -2.750  -0.1130   0.03381   0.02832  -0.0235   1.0000   0.1460
  -2.500  -0.0761   0.03152   0.02601  -0.0272   0.8774   0.1897
  -2.250  -0.0594   0.03019   0.02412  -0.0248   0.7157   0.2268
  -2.000  -0.0375   0.02950   0.02303  -0.0241   0.6648   0.2842
  -1.750  -0.0183   0.02721   0.02080  -0.0228   0.6316   0.3305
  -1.500   0.0042   0.02567   0.01919  -0.0217   0.6039   0.3841
  -1.250   0.0267   0.02394   0.01746  -0.0202   0.5807   0.4266
  -1.000   0.0618   0.02277   0.01591  -0.0215   0.5574   0.4291
  -0.750   0.1021   0.02194   0.01448  -0.0236   0.5360   0.3952
  -0.500   0.1466   0.02169   0.01332  -0.0252   0.5160   0.3102
  -0.250   0.1861   0.02192   0.01276  -0.0249   0.4971   0.2318
   0.000   0.2203   0.02212   0.01239  -0.0239   0.4796   0.1860
   0.250   0.2507   0.02156   0.01160  -0.0233   0.4634   0.1665
   0.500   0.2808   0.02130   0.01109  -0.0226   0.4484   0.1495
   0.750   0.3103   0.02119   0.01073  -0.0218   0.4352   0.1350
   1.000   0.3400   0.02137   0.01067  -0.0211   0.4226   0.1236
   1.250   0.3685   0.02085   0.01024  -0.0207   0.4116   0.1176
   1.500   0.3967   0.02085   0.01010  -0.0201   0.4027   0.1116
   1.750   0.4249   0.02086   0.01013  -0.0197   0.3924   0.1089
   2.000   0.4522   0.02077   0.01006  -0.0192   0.3840   0.1096
   2.250   0.4798   0.02069   0.00995  -0.0187   0.3750   0.1098
   2.500   0.5082   0.02078   0.01000  -0.0185   0.3658   0.1093
   2.750   0.5364   0.02082   0.00990  -0.0182   0.3575   0.1099
   3.000   0.5651   0.02103   0.01011  -0.0181   0.3487   0.1122
   3.250   0.5932   0.02120   0.01017  -0.0178   0.3416   0.1184
   3.500   0.6220   0.02151   0.01066  -0.0178   0.3342   0.1463
   3.750   0.6455   0.02008   0.01095  -0.0167   0.3276   1.0000
   4.000   0.6732   0.02063   0.01141  -0.0164   0.3209   1.0000
   4.250   0.7008   0.02113   0.01185  -0.0162   0.3130   1.0000
   4.500   0.7280   0.02165   0.01224  -0.0159   0.3065   1.0000
   4.750   0.7555   0.02228   0.01292  -0.0158   0.2983   1.0000
   5.000   0.7823   0.02282   0.01327  -0.0154   0.2930   1.0000
   5.250   0.8095   0.02381   0.01451  -0.0156   0.2850   1.0000
   5.500   0.8362   0.02443   0.01503  -0.0153   0.2794   1.0000
   5.750   0.8626   0.02568   0.01647  -0.0154   0.2730   1.0000
   6.000   0.8889   0.02670   0.01762  -0.0154   0.2671   1.0000
   6.250   0.9152   0.02746   0.01826  -0.0150   0.2627   1.0000
   6.500   0.9399   0.02930   0.02053  -0.0155   0.2560   1.0000
   6.750   0.9652   0.03049   0.02185  -0.0154   0.2511   1.0000
   7.000   0.9908   0.03151   0.02285  -0.0151   0.2477   1.0000
   7.250   1.0128   0.03421   0.02598  -0.0158   0.2436   1.0000
   7.500   1.0333   0.03715   0.02937  -0.0167   0.2384   1.0000
   7.750   1.0608   0.03657   0.02861  -0.0155   0.2331   1.0000
   8.000   1.0798   0.03891   0.03133  -0.0161   0.2251   1.0000
   8.250   1.1077   0.03791   0.03016  -0.0148   0.2182   1.0000
   8.500   1.1276   0.03974   0.03226  -0.0150   0.2116   1.0000
   8.750   1.1498   0.04063   0.03334  -0.0147   0.2045   1.0000
   9.000   1.1778   0.03992   0.03242  -0.0135   0.1989   1.0000
   9.250   1.1933   0.04220   0.03521  -0.0139   0.1900   1.0000
   9.500   1.2220   0.04103   0.03388  -0.0126   0.1832   1.0000
   9.750   1.2445   0.04102   0.03406  -0.0120   0.1734   1.0000
  10.000   1.2643   0.04158   0.03483  -0.0116   0.1629   1.0000
  10.250   1.2901   0.04057   0.03378  -0.0105   0.1518   1.0000
  10.500   1.3158   0.03958   0.03270  -0.0095   0.1403   1.0000
  10.750   1.3404   0.03910   0.03201  -0.0086   0.1294   1.0000
  11.000   1.3571   0.04020   0.03325  -0.0081   0.1191   1.0000
  11.250   1.3645   0.04320   0.03663  -0.0079   0.1111   1.0000
  11.500   1.3850   0.04382   0.03702  -0.0070   0.1037   1.0000
  11.750   1.3817   0.04785   0.04164  -0.0073   0.0986   1.0000
  12.000   1.4046   0.04810   0.04153  -0.0061   0.0922   1.0000
  12.250   1.3900   0.05301   0.04702  -0.0069   0.0899   1.0000
  12.500   1.3667   0.05849   0.05284  -0.0086   0.0889   1.0000
  12.750   1.3312   0.06752   0.06216  -0.0158   0.0897   1.0000
  13.000   1.2858   0.07985   0.07467  -0.0253   0.0915   1.0000
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