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GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 63 AIRFOIL (goe63-il)
Reynolds number: 50,000
Max Cl/Cd: 30.44 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe63-il-50000.txt
Download as CSV file: xf-goe63-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 63 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2459   0.12295   0.11592  -0.0257   1.0000   0.0892
  -9.250  -0.2412   0.12096   0.11399  -0.0268   1.0000   0.0916
  -9.000  -0.2408   0.12020   0.11334  -0.0283   1.0000   0.0935
  -8.750  -0.2467   0.12071   0.11399  -0.0296   1.0000   0.0943
  -8.500  -0.2579   0.12159   0.11505  -0.0298   1.0000   0.0946
  -8.250  -0.2322   0.11295   0.10641  -0.0286   1.0000   0.0967
  -8.000  -0.2283   0.11013   0.10369  -0.0275   1.0000   0.0986
  -7.750  -0.2331   0.10872   0.10243  -0.0256   1.0000   0.1002
  -7.500  -0.2471   0.10837   0.10224  -0.0223   1.0000   0.1011
  -7.250  -0.2668   0.10863   0.10265  -0.0182   1.0000   0.1017
  -7.000  -0.2836   0.10860   0.10275  -0.0150   1.0000   0.1024
  -6.750  -0.2976   0.10830   0.10255  -0.0127   1.0000   0.1034
  -6.500  -0.3088   0.10781   0.10215  -0.0114   1.0000   0.1046
  -6.250  -0.3173   0.10736   0.10178  -0.0112   1.0000   0.1060
  -6.000  -0.3222   0.10747   0.10193  -0.0134   1.0000   0.1073
  -5.750  -0.3182   0.10856   0.10300  -0.0201   1.0000   0.1081
  -5.500  -0.3213   0.10344   0.09799  -0.0146   1.0000   0.1091
  -5.250  -0.3214   0.10022   0.09482  -0.0119   1.0000   0.1109
  -5.000  -0.3189   0.09789   0.09253  -0.0112   1.0000   0.1133
  -4.750  -0.3134   0.09590   0.09055  -0.0122   1.0000   0.1166
  -4.500  -0.2867   0.09656   0.09106  -0.0236   1.0000   0.1221
  -4.250  -0.2859   0.09236   0.08696  -0.0209   1.0000   0.1236
  -4.000  -0.2833   0.08919   0.08384  -0.0186   1.0000   0.1266
  -3.750  -0.2715   0.08698   0.08163  -0.0201   1.0000   0.1318
  -3.500  -0.2253   0.08418   0.07870  -0.0312   0.9939   0.1393
  -3.250  -0.2034   0.08079   0.07532  -0.0330   0.9882   0.1457
  -3.000  -0.1568   0.07812   0.07250  -0.0429   0.9817   0.1559
  -2.750  -0.1094   0.07658   0.07078  -0.0525   0.9741   0.1702
  -2.500  -0.0911   0.07254   0.06683  -0.0524   0.9685   0.1775
  -2.000  -0.0055   0.06850   0.06256  -0.0670   0.9527   0.2192
  -1.750   0.0319   0.06673   0.06070  -0.0721   0.9438   0.2511
  -1.500   0.0539   0.06319   0.05728  -0.0724   0.9354   0.2746
  -1.250   0.0908   0.06062   0.05475  -0.0759   0.9252   0.3283
  -0.750   0.1309   0.05535   0.04973  -0.0732   0.9047   0.4810
  -0.500   0.1510   0.05285   0.04734  -0.0714   0.8940   0.5484
  -0.250   0.1749   0.05071   0.04527  -0.0707   0.8831   0.6041
   0.000   0.2250   0.04828   0.04283  -0.0747   0.8728   0.6620
   0.250   0.2539   0.04675   0.04135  -0.0759   0.8602   0.6913
   0.500   0.3122   0.04564   0.04015  -0.0840   0.8468   0.7043
   0.750   0.4610   0.04731   0.04081  -0.1149   0.8275   0.5346
   1.000   0.5480   0.04913   0.04152  -0.1275   0.8110   0.3530
   1.250   0.6029   0.04885   0.04071  -0.1315   0.7971   0.2757
   1.500   0.6772   0.04747   0.03875  -0.1369   0.7867   0.2284
   1.750   0.7094   0.04745   0.03846  -0.1370   0.7711   0.2097
   2.000   0.7437   0.04735   0.03810  -0.1372   0.7555   0.1954
   2.250   0.7780   0.04738   0.03776  -0.1369   0.7401   0.1851
   2.500   0.8111   0.04707   0.03725  -0.1365   0.7252   0.1829
   2.750   0.8474   0.04656   0.03652  -0.1359   0.7114   0.1852
   3.000   0.8931   0.04501   0.03485  -0.1357   0.7006   0.1883
   3.250   0.9173   0.04508   0.03492  -0.1342   0.6846   0.1938
   3.500   0.9420   0.04517   0.03501  -0.1328   0.6688   0.2071
   3.750   0.9666   0.04534   0.03524  -0.1316   0.6533   0.2270
   4.000   0.9936   0.04522   0.03556  -0.1309   0.6386   0.3011
   4.250   1.0326   0.04299   0.03366  -0.1282   0.6303   1.0000
   4.500   1.0553   0.04355   0.03393  -0.1265   0.6154   1.0000
   4.750   1.0738   0.04447   0.03472  -0.1249   0.5999   1.0000
   5.000   1.0918   0.04546   0.03563  -0.1232   0.5848   1.0000
   5.250   1.1114   0.04628   0.03639  -0.1216   0.5706   1.0000
   5.500   1.1425   0.04588   0.03590  -0.1203   0.5589   1.0000
   5.750   1.1807   0.04463   0.03453  -0.1192   0.5481   1.0000
   6.000   1.1949   0.04592   0.03586  -0.1175   0.5334   1.0000
   6.250   1.2100   0.04713   0.03709  -0.1158   0.5194   1.0000
   6.500   1.2316   0.04761   0.03757  -0.1142   0.5064   1.0000
   6.750   1.2851   0.04468   0.03449  -0.1137   0.4969   1.0000
   7.000   1.3047   0.04533   0.03517  -0.1121   0.4830   1.0000
   7.250   1.3183   0.04668   0.03659  -0.1103   0.4691   1.0000
   7.500   1.3341   0.04783   0.03780  -0.1086   0.4558   1.0000
   7.750   1.3601   0.04793   0.03792  -0.1073   0.4430   1.0000
   8.000   1.4002   0.04678   0.03665  -0.1068   0.4308   1.0000
   8.250   1.4282   0.04692   0.03675  -0.1057   0.4178   1.0000
   8.500   1.4291   0.04970   0.03975  -0.1034   0.4052   1.0000
   8.750   1.4366   0.05199   0.04214  -0.1015   0.3938   1.0000
   9.000   1.4745   0.05156   0.04162  -0.1011   0.3820   1.0000
   9.250   1.4783   0.05418   0.04439  -0.0990   0.3712   1.0000
   9.500   1.4593   0.05899   0.04943  -0.0959   0.3629   1.0000
   9.750   1.5265   0.05655   0.04679  -0.0973   0.3513   1.0000
  10.000   1.4094   0.06988   0.06060  -0.0904   0.3491   1.0000
  10.250   1.0024   0.14128   0.13215  -0.1214   0.4206   1.0000
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