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GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 B AIRFOIL (goe802b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103.3 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802b-il-1000000-n5.txt
Download as CSV file: xf-goe802b-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 B 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2492   0.10594   0.10401  -0.0394   0.8922   0.0092
 -10.000  -0.2434   0.10258   0.10062  -0.0409   0.8840   0.0096
  -9.750  -0.2435   0.09743   0.09543  -0.0433   0.8754   0.0103
  -9.500  -0.2344   0.09509   0.09306  -0.0446   0.8679   0.0104
  -9.250  -0.2248   0.09275   0.09071  -0.0460   0.8605   0.0105
  -9.000  -0.2153   0.09041   0.08833  -0.0474   0.8527   0.0106
  -8.750  -0.2057   0.08794   0.08584  -0.0491   0.8458   0.0108
  -8.500  -0.1963   0.08535   0.08324  -0.0509   0.8383   0.0110
  -8.000  -0.1741   0.07975   0.07759  -0.0564   0.8248   0.0118
  -7.750  -0.1599   0.07593   0.07373  -0.0609   0.8174   0.0123
  -7.500  -0.1440   0.06997   0.06771  -0.0684   0.8105   0.0131
  -7.250  -0.1246   0.06748   0.06520  -0.0717   0.8042   0.0132
  -7.000  -0.1042   0.06495   0.06263  -0.0751   0.7973   0.0133
  -6.750  -0.0827   0.06232   0.05993  -0.0786   0.7907   0.0136
  -6.500  -0.0598   0.05953   0.05711  -0.0823   0.7836   0.0139
  -6.250  -0.0360   0.05667   0.05418  -0.0860   0.7758   0.0144
  -6.000  -0.0103   0.05320   0.05062  -0.0903   0.7690   0.0150
  -5.750   0.0237   0.04637   0.04362  -0.0981   0.7615   0.0161
  -5.500   0.0482   0.04408   0.04122  -0.1003   0.7517   0.0162
  -5.250   0.0734   0.04224   0.03929  -0.1021   0.7390   0.0164
  -5.000   0.0989   0.04052   0.03746  -0.1037   0.7243   0.0166
  -4.750   0.1249   0.03879   0.03561  -0.1053   0.7093   0.0170
  -4.500   0.1522   0.03664   0.03332  -0.1071   0.6958   0.0175
  -4.250   0.1807   0.03420   0.03073  -0.1089   0.6839   0.0179
  -4.000   0.2092   0.03180   0.02815  -0.1104   0.6721   0.0183
  -3.750   0.2381   0.02940   0.02555  -0.1117   0.6584   0.0187
  -3.500   0.2672   0.02693   0.02284  -0.1128   0.6442   0.0190
  -3.250   0.2970   0.02398   0.01955  -0.1137   0.6304   0.0197
  -3.000   0.3238   0.02286   0.01827  -0.1142   0.6156   0.0199
  -2.750   0.3508   0.02198   0.01727  -0.1146   0.6021   0.0201
  -2.500   0.3781   0.02111   0.01626  -0.1150   0.5897   0.0204
  -2.250   0.4054   0.02024   0.01524  -0.1154   0.5765   0.0207
  -2.000   0.4331   0.01928   0.01410  -0.1157   0.5630   0.0211
  -1.750   0.4610   0.01829   0.01294  -0.1160   0.5511   0.0213
  -1.250   0.5172   0.01629   0.01057  -0.1165   0.5307   0.0217
  -0.750   0.5734   0.01195   0.00542  -0.1170   0.5143   0.0230
  -0.500   0.6001   0.01124   0.00455  -0.1172   0.5054   0.0234
  -0.250   0.6270   0.01089   0.00412  -0.1173   0.4969   0.0236
   0.000   0.6539   0.01042   0.00356  -0.1175   0.4874   0.0240
   0.250   0.6810   0.01025   0.00333  -0.1176   0.4779   0.0243
   0.500   0.7084   0.01012   0.00317  -0.1178   0.4687   0.0246
   0.750   0.7355   0.01005   0.00306  -0.1178   0.4598   0.0249
   1.000   0.7630   0.00997   0.00298  -0.1180   0.4518   0.0254
   1.250   0.7901   0.00995   0.00293  -0.1180   0.4425   0.0260
   1.500   0.8176   0.00992   0.00289  -0.1181   0.4345   0.0265
   1.750   0.8447   0.00997   0.00289  -0.1181   0.4237   0.0270
   2.000   0.8718   0.01004   0.00292  -0.1181   0.4103   0.0275
   2.250   0.8983   0.01018   0.00299  -0.1180   0.3930   0.0280
   2.500   0.9250   0.01036   0.00311  -0.1179   0.3781   0.0286
   2.750   0.9519   0.01053   0.00324  -0.1178   0.3664   0.0297
   3.000   0.9787   0.01064   0.00333  -0.1178   0.3561   0.0309
   3.250   1.0048   0.01078   0.00343  -0.1177   0.3444   0.0322
   3.500   1.0312   0.01086   0.00351  -0.1176   0.3341   0.0347
   3.750   1.0576   0.01114   0.00381  -0.1175   0.3227   0.0537
   4.000   1.0835   0.01122   0.00387  -0.1174   0.3126   0.0623
   4.250   1.1094   0.01136   0.00399  -0.1173   0.3046   0.0653
   4.500   1.1361   0.01148   0.00412  -0.1173   0.2990   0.0673
   4.750   1.1620   0.01160   0.00422  -0.1172   0.2922   0.0691
   5.000   1.1880   0.01175   0.00437  -0.1170   0.2858   0.0712
   5.250   1.2141   0.01190   0.00453  -0.1169   0.2796   0.0745
   5.500   1.2390   0.01209   0.00469  -0.1167   0.2695   0.0753
   5.750   1.2640   0.01224   0.00482  -0.1164   0.2559   0.0758
   6.000   1.2881   0.01247   0.00500  -0.1161   0.2403   0.0762
   6.250   1.3116   0.01276   0.00521  -0.1156   0.2230   0.0765
   6.500   1.3339   0.01314   0.00550  -0.1150   0.2012   0.0770
   6.750   1.3543   0.01367   0.00588  -0.1140   0.1748   0.0775
   7.000   1.3754   0.01412   0.00625  -0.1132   0.1563   0.0781
   7.250   1.3966   0.01454   0.00661  -0.1124   0.1414   0.0786
   7.500   1.4177   0.01495   0.00696  -0.1116   0.1291   0.0791
   8.000   1.4610   0.01563   0.00760  -0.1101   0.1126   0.0800
   8.250   1.4819   0.01600   0.00796  -0.1092   0.1035   0.0807
   8.500   1.5009   0.01648   0.00839  -0.1081   0.0921   0.0820
   9.000   1.5313   0.01781   0.00955  -0.1045   0.0626   0.0836
   9.250   1.5446   0.01829   0.01003  -0.1023   0.0564   0.0843
   9.750   1.5731   0.01940   0.01116  -0.0984   0.0477   0.0862
  10.000   1.5895   0.01991   0.01170  -0.0970   0.0451   0.0868
  10.250   1.6017   0.02069   0.01246  -0.0950   0.0389   0.0869
  10.500   1.6007   0.02235   0.01400  -0.0913   0.0165   0.0869
  10.750   1.6125   0.02322   0.01492  -0.0895   0.0144   0.0870
  11.000   1.6248   0.02408   0.01584  -0.0879   0.0127   0.0872
  11.250   1.6378   0.02491   0.01674  -0.0864   0.0121   0.0877
  11.500   1.6495   0.02586   0.01774  -0.0849   0.0113   0.0881
  11.750   1.6601   0.02692   0.01886  -0.0833   0.0106   0.0883
  12.000   1.6694   0.02810   0.02011  -0.0817   0.0099   0.0884
  12.250   1.6783   0.02936   0.02144  -0.0802   0.0094   0.0884
  12.500   1.6885   0.03055   0.02270  -0.0789   0.0092   0.0885
  12.750   1.6976   0.03186   0.02408  -0.0776   0.0089   0.0887
  13.000   1.7056   0.03331   0.02559  -0.0763   0.0086   0.0890
  13.250   1.7125   0.03488   0.02724  -0.0750   0.0083   0.0894
  13.500   1.7183   0.03659   0.02903  -0.0738   0.0080   0.0897
  13.750   1.7232   0.03844   0.03095  -0.0726   0.0077   0.0898
  14.000   1.7266   0.04050   0.03308  -0.0715   0.0074   0.0899
  14.250   1.7286   0.04276   0.03541  -0.0705   0.0071   0.0901
  14.500   1.7285   0.04532   0.03806  -0.0695   0.0068   0.0903
  14.750   1.7303   0.04780   0.04062  -0.0688   0.0067   0.0906
  15.000   1.7321   0.05032   0.04323  -0.0683   0.0066   0.0910
  15.250   1.7329   0.05304   0.04604  -0.0679   0.0064   0.0913
  15.500   1.7327   0.05597   0.04906  -0.0676   0.0063   0.0915
  16.000   1.7289   0.06249   0.05577  -0.0674   0.0060   0.0918
  16.250   1.7253   0.06604   0.05941  -0.0674   0.0059   0.0924
  16.500   1.7209   0.06979   0.06327  -0.0677   0.0058   0.0930
  16.750   1.7155   0.07374   0.06732  -0.0680   0.0057   0.0934
  17.000   1.7091   0.07787   0.07155  -0.0685   0.0056   0.0935
  17.250   1.7017   0.08220   0.07597  -0.0691   0.0055   0.0937
  17.500   1.6936   0.08667   0.08055  -0.0698   0.0054   0.0940
  17.750   1.6847   0.09135   0.08532  -0.0707   0.0053   0.0944
  18.000   1.6751   0.09615   0.09023  -0.0717   0.0052   0.0948
  18.250   1.6645   0.10116   0.09534  -0.0729   0.0052   0.0952
  18.500   1.6534   0.10636   0.10064  -0.0743   0.0051   0.0956
  18.750   1.6421   0.11164   0.10603  -0.0758   0.0050   0.0958
  19.000   1.6302   0.11707   0.11157  -0.0776   0.0050   0.0961
  19.250   1.6180   0.12262   0.11722  -0.0795   0.0049   0.0964
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