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GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 456 AIRFOIL (goe456-il)
Reynolds number: 500,000
Max Cl/Cd: 115.61 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe456-il-500000-n5.txt
Download as CSV file: xf-goe456-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 456 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3002   0.12037   0.11809  -0.0341   1.0000   0.0046
 -10.000  -0.2983   0.11745   0.11521  -0.0341   1.0000   0.0043
  -9.750  -0.2969   0.11466   0.11244  -0.0340   1.0000   0.0042
  -9.500  -0.2898   0.11136   0.10915  -0.0355   0.9993   0.0042
  -9.250  -0.2760   0.10722   0.10501  -0.0391   0.9970   0.0041
  -9.000  -0.2629   0.10313   0.10093  -0.0425   0.9930   0.0044
  -8.750  -0.2494   0.09938   0.09717  -0.0459   0.9888   0.0043
  -8.000  -0.1997   0.08987   0.08768  -0.0586   0.9707   0.0060
  -7.750  -0.1825   0.08574   0.08355  -0.0632   0.9661   0.0060
  -7.500  -0.1649   0.08177   0.07957  -0.0678   0.9589   0.0060
  -7.250  -0.1443   0.07742   0.07521  -0.0735   0.9524   0.0060
  -7.000  -0.1237   0.07313   0.07090  -0.0793   0.9433   0.0060
  -6.750  -0.1075   0.06775   0.06549  -0.0847   0.9333   0.0056
  -6.500  -0.0882   0.06324   0.06094  -0.0907   0.9216   0.0054
  -6.250  -0.0702   0.05907   0.05672  -0.0960   0.9092   0.0052
  -6.000  -0.0521   0.05483   0.05241  -0.1011   0.8969   0.0051
  -5.750  -0.0328   0.05062   0.04811  -0.1060   0.8859   0.0050
  -5.500  -0.0117   0.04603   0.04342  -0.1110   0.8756   0.0049
  -5.250   0.0117   0.04135   0.03862  -0.1158   0.8661   0.0047
  -5.000   0.0378   0.03604   0.03314  -0.1206   0.8574   0.0046
  -4.750   0.0660   0.02900   0.02581  -0.1252   0.8492   0.0045
  -4.500   0.0922   0.02192   0.01815  -0.1279   0.8413   0.0044
  -4.250   0.1172   0.01767   0.01323  -0.1284   0.8341   0.0044
  -4.000   0.1425   0.01458   0.00949  -0.1280   0.8267   0.0048
  -3.750   0.1689   0.01297   0.00743  -0.1275   0.8196   0.0057
  -3.500   0.1948   0.01197   0.00623  -0.1273   0.8116   0.0066
  -3.250   0.2213   0.01175   0.00596  -0.1272   0.8037   0.0079
  -3.000   0.2480   0.01167   0.00578  -0.1271   0.7953   0.0109
  -2.750   0.2747   0.01080   0.00470  -0.1267   0.7870   0.0123
  -2.500   0.3015   0.01040   0.00410  -0.1263   0.7783   0.0140
  -2.250   0.3279   0.01000   0.00358  -0.1260   0.7683   0.0162
  -2.000   0.3540   0.00952   0.00303  -0.1257   0.7579   0.0180
  -1.750   0.3804   0.00925   0.00268  -0.1254   0.7472   0.0197
  -1.500   0.4068   0.00906   0.00241  -0.1251   0.7362   0.0216
  -1.250   0.4332   0.00885   0.00209  -0.1247   0.7243   0.0212
  -0.750   0.4860   0.00862   0.00156  -0.1240   0.6985   0.0203
  -0.500   0.5124   0.00859   0.00141  -0.1237   0.6860   0.0200
  -0.250   0.5388   0.00857   0.00131  -0.1233   0.6743   0.0197
   0.000   0.5649   0.00859   0.00124  -0.1229   0.6609   0.0195
   0.250   0.5906   0.00865   0.00119  -0.1225   0.6455   0.0194
   0.500   0.6163   0.00872   0.00118  -0.1221   0.6308   0.0197
   0.750   0.6423   0.00879   0.00117  -0.1217   0.6183   0.0202
   1.000   0.6683   0.00885   0.00118  -0.1214   0.6066   0.0219
   1.250   0.6940   0.00868   0.00124  -0.1211   0.5963   0.1371
   1.500   0.7196   0.00863   0.00136  -0.1208   0.5864   0.1997
   1.750   0.7439   0.00819   0.00161  -0.1205   0.5765   0.4599
   2.000   0.7765   0.00725   0.00176  -0.1218   0.5648   1.0000
   2.250   0.8019   0.00739   0.00184  -0.1214   0.5521   1.0000
   2.500   0.8275   0.00753   0.00193  -0.1210   0.5412   1.0000
   2.750   0.8532   0.00767   0.00204  -0.1206   0.5322   1.0000
   3.000   0.8792   0.00778   0.00215  -0.1203   0.5233   1.0000
   3.250   0.9049   0.00792   0.00233  -0.1200   0.5146   1.0000
   3.750   0.9549   0.00826   0.00263  -0.1190   0.4847   1.0000
   4.000   0.9672   0.00930   0.00300  -0.1163   0.3567   1.0000
   4.250   0.9805   0.01049   0.00363  -0.1141   0.2491   1.0000
   4.500   0.9869   0.01235   0.00456  -0.1108   0.0879   1.0000
   4.750   1.0011   0.01352   0.00539  -0.1085   0.0046   1.0000
   5.000   1.0226   0.01405   0.00606  -0.1073   0.0028   1.0000
   5.250   1.0441   0.01454   0.00665  -0.1062   0.0027   1.0000
   5.500   1.0640   0.01518   0.00739  -0.1047   0.0025   1.0000
   5.750   1.0821   0.01596   0.00827  -0.1030   0.0024   1.0000
   6.000   1.0986   0.01685   0.00926  -0.1010   0.0023   1.0000
   6.250   1.1134   0.01781   0.01031  -0.0987   0.0023   1.0000
   6.500   1.1258   0.01892   0.01164  -0.0960   0.0023   1.0000
   6.750   1.1370   0.02011   0.01292  -0.0932   0.0023   1.0000
   7.000   1.1466   0.02136   0.01426  -0.0901   0.0023   1.0000
   7.250   1.1576   0.02272   0.01569  -0.0873   0.0024   1.0000
   7.500   1.1719   0.02424   0.01730  -0.0851   0.0024   1.0000
   7.750   1.1915   0.02604   0.01919  -0.0839   0.0024   1.0000
   8.000   1.2176   0.02828   0.02156  -0.0838   0.0025   1.0000
   8.250   1.2440   0.03087   0.02431  -0.0837   0.0026   1.0000
   8.500   1.2681   0.03435   0.02801  -0.0833   0.0028   1.0000
   9.500   1.3327   0.04235   0.03678  -0.0761   0.0036   1.0000
   9.750   1.3382   0.04512   0.03982  -0.0732   0.0037   1.0000
  10.000   1.3391   0.04774   0.04267  -0.0697   0.0037   1.0000
  10.250   1.3348   0.05024   0.04539  -0.0657   0.0037   1.0000
  10.500   1.3273   0.05290   0.04835  -0.0617   0.0037   1.0000
  10.750   1.3175   0.05564   0.05130  -0.0581   0.0037   1.0000
  11.000   1.3062   0.05851   0.05436  -0.0549   0.0036   1.0000
  11.250   1.2930   0.06176   0.05781  -0.0523   0.0036   1.0000
  11.500   1.2791   0.06521   0.06145  -0.0503   0.0036   1.0000
  11.750   1.2641   0.06905   0.06547  -0.0489   0.0036   1.0000
  12.000   1.2481   0.07327   0.06987  -0.0482   0.0036   1.0000
  12.250   1.2312   0.07798   0.07476  -0.0482   0.0036   1.0000
  12.500   1.2137   0.08312   0.08007  -0.0491   0.0036   1.0000
  12.750   1.1957   0.08876   0.08588  -0.0507   0.0037   1.0000
  13.000   1.1773   0.09494   0.09221  -0.0531   0.0037   1.0000
  13.250   1.1583   0.10180   0.09923  -0.0564   0.0037   1.0000
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