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GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.87 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe300-il-1000000-n5.txt
Download as CSV file: xf-goe300-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2337   0.09167   0.08962  -0.0411   0.8460   0.0068
  -8.750  -0.2258   0.08889   0.08680  -0.0426   0.8335   0.0069
  -8.250  -0.2485   0.06683   0.06462  -0.0645   0.8081   0.0088
  -8.000  -0.2350   0.05485   0.05245  -0.0811   0.7963   0.0094
  -7.750  -0.2121   0.04822   0.04563  -0.0897   0.7840   0.0098
  -7.500  -0.1866   0.03997   0.03706  -0.0992   0.7721   0.0103
  -7.250  -0.1606   0.03577   0.03263  -0.1032   0.7584   0.0107
  -7.000  -0.1343   0.03265   0.02930  -0.1058   0.7432   0.0111
  -6.750  -0.1080   0.02931   0.02575  -0.1082   0.7280   0.0116
  -6.500  -0.0828   0.02310   0.01905  -0.1117   0.7149   0.0123
  -6.250  -0.0593   0.01718   0.01249  -0.1137   0.7017   0.0130
  -6.000  -0.0354   0.01337   0.00818  -0.1144   0.6877   0.0138
  -5.750  -0.0096   0.01162   0.00617  -0.1146   0.6731   0.0149
  -5.500   0.0177   0.01101   0.00541  -0.1145   0.6604   0.0160
  -5.250   0.0453   0.01057   0.00483  -0.1144   0.6489   0.0171
  -5.000   0.0727   0.01011   0.00425  -0.1143   0.6355   0.0189
  -4.750   0.1004   0.00982   0.00385  -0.1142   0.6210   0.0209
  -4.500   0.1280   0.00949   0.00344  -0.1141   0.6087   0.0243
  -4.250   0.1558   0.00927   0.00316  -0.1140   0.5987   0.0285
  -4.000   0.1838   0.00915   0.00299  -0.1139   0.5879   0.0325
  -3.750   0.2120   0.00916   0.00299  -0.1138   0.5775   0.0368
  -3.500   0.2401   0.00916   0.00291  -0.1137   0.5678   0.0393
  -3.250   0.2683   0.00911   0.00280  -0.1136   0.5586   0.0406
  -3.000   0.2966   0.00912   0.00279  -0.1135   0.5512   0.0428
  -2.750   0.3250   0.00917   0.00282  -0.1134   0.5438   0.0445
  -2.500   0.3532   0.00920   0.00281  -0.1133   0.5367   0.0460
  -2.250   0.3816   0.00919   0.00276  -0.1133   0.5304   0.0475
  -2.000   0.4098   0.00920   0.00272  -0.1132   0.5242   0.0487
  -1.750   0.4380   0.00920   0.00267  -0.1131   0.5187   0.0494
  -1.500   0.4663   0.00918   0.00262  -0.1131   0.5131   0.0499
  -1.250   0.4942   0.00908   0.00246  -0.1130   0.5057   0.0504
  -1.000   0.5220   0.00888   0.00220  -0.1129   0.4979   0.0519
  -0.750   0.5499   0.00883   0.00211  -0.1128   0.4892   0.0530
  -0.500   0.5780   0.00880   0.00206  -0.1128   0.4828   0.0541
  -0.250   0.6059   0.00881   0.00203  -0.1127   0.4742   0.0552
   0.000   0.6338   0.00880   0.00199  -0.1126   0.4648   0.0560
   0.250   0.6614   0.00882   0.00195  -0.1125   0.4536   0.0567
   0.500   0.6891   0.00884   0.00192  -0.1125   0.4416   0.0574
   0.750   0.7167   0.00888   0.00190  -0.1124   0.4289   0.0581
   1.000   0.7440   0.00895   0.00191  -0.1122   0.4137   0.0588
   1.250   0.7711   0.00906   0.00193  -0.1121   0.3966   0.0594
   1.500   0.7978   0.00921   0.00198  -0.1119   0.3775   0.0600
   1.750   0.8248   0.00933   0.00204  -0.1117   0.3630   0.0606
   2.000   0.8519   0.00943   0.00210  -0.1116   0.3529   0.0612
   2.250   0.8789   0.00954   0.00216  -0.1115   0.3428   0.0641
   2.500   0.9062   0.00963   0.00225  -0.1114   0.3346   0.0672
   2.750   0.9331   0.00976   0.00235  -0.1112   0.3270   0.0700
   3.000   0.9605   0.00983   0.00243  -0.1111   0.3227   0.0722
   3.250   0.9878   0.00992   0.00252  -0.1111   0.3180   0.0761
   3.500   1.0148   0.01003   0.00264  -0.1110   0.3132   0.0816
   3.750   1.0419   0.01014   0.00275  -0.1109   0.3092   0.0859
   4.000   1.0691   0.01021   0.00287  -0.1108   0.3058   0.0932
   4.250   1.0961   0.01031   0.00298  -0.1107   0.3019   0.0996
   4.500   1.1228   0.01045   0.00313  -0.1106   0.2968   0.1076
   4.750   1.1494   0.01058   0.00327  -0.1104   0.2915   0.1157
   5.000   1.1761   0.01069   0.00342  -0.1103   0.2858   0.1285
   5.250   1.2024   0.01084   0.00359  -0.1102   0.2796   0.1523
   5.750   1.2522   0.00987   0.00411  -0.1096   0.2689   1.0000
   6.000   1.2778   0.01010   0.00429  -0.1093   0.2601   1.0000
   6.250   1.3029   0.01038   0.00450  -0.1090   0.2472   1.0000
   6.500   1.3260   0.01083   0.00480  -0.1084   0.2192   1.0000
   6.750   1.3448   0.01165   0.00536  -0.1072   0.1772   1.0000
   7.000   1.3685   0.01201   0.00568  -0.1067   0.1685   1.0000
   7.250   1.3920   0.01237   0.00601  -0.1061   0.1614   1.0000
   7.500   1.4165   0.01263   0.00628  -0.1057   0.1580   1.0000
   7.750   1.4406   0.01291   0.00656  -0.1053   0.1547   1.0000
   8.000   1.4637   0.01325   0.00690  -0.1047   0.1498   1.0000
   8.250   1.4865   0.01362   0.00726  -0.1040   0.1435   1.0000
   8.500   1.5098   0.01391   0.00756  -0.1035   0.1389   1.0000
   8.750   1.5317   0.01430   0.00793  -0.1028   0.1327   1.0000
   9.000   1.5537   0.01466   0.00830  -0.1020   0.1279   1.0000
   9.250   1.5756   0.01500   0.00865  -0.1013   0.1220   1.0000
   9.500   1.5952   0.01550   0.00910  -0.1002   0.1130   1.0000
   9.750   1.6137   0.01603   0.00958  -0.0990   0.1027   1.0000
  10.000   1.6292   0.01669   0.01017  -0.0974   0.0904   1.0000
  10.250   1.6399   0.01749   0.01089  -0.0949   0.0773   1.0000
  10.500   1.6469   0.01851   0.01183  -0.0920   0.0614   1.0000
  10.750   1.6385   0.02053   0.01363  -0.0872   0.0284   1.0000
  11.000   1.6445   0.02176   0.01486  -0.0847   0.0205   1.0000
  11.250   1.6530   0.02288   0.01601  -0.0827   0.0169   1.0000
  11.500   1.6620   0.02402   0.01718  -0.0808   0.0146   1.0000
  11.750   1.6715   0.02517   0.01838  -0.0792   0.0129   1.0000
  12.000   1.6802   0.02644   0.01968  -0.0776   0.0115   1.0000
  12.250   1.6888   0.02775   0.02104  -0.0761   0.0104   1.0000
  12.500   1.6957   0.02926   0.02261  -0.0747   0.0095   1.0000
  12.750   1.7037   0.03074   0.02415  -0.0734   0.0088   1.0000
  13.000   1.7102   0.03240   0.02588  -0.0722   0.0082   1.0000
  13.250   1.7151   0.03427   0.02781  -0.0711   0.0077   1.0000
  13.500   1.7193   0.03627   0.02989  -0.0701   0.0073   1.0000
  13.750   1.7237   0.03831   0.03200  -0.0692   0.0070   1.0000
  14.000   1.7268   0.04054   0.03430  -0.0684   0.0066   1.0000
  14.250   1.7285   0.04299   0.03683  -0.0677   0.0063   1.0000
  14.500   1.7285   0.04569   0.03960  -0.0671   0.0060   1.0000
  14.750   1.7271   0.04861   0.04260  -0.0666   0.0057   1.0000
  15.000   1.7272   0.05146   0.04555  -0.0663   0.0055   1.0000
  15.250   1.7262   0.05451   0.04870  -0.0661   0.0053   1.0000
  15.500   1.7238   0.05779   0.05207  -0.0660   0.0051   1.0000
  15.750   1.7201   0.06128   0.05565  -0.0660   0.0050   1.0000
  16.000   1.7153   0.06498   0.05944  -0.0661   0.0048   1.0000
  16.250   1.7097   0.06887   0.06342  -0.0664   0.0047   1.0000
  16.500   1.7026   0.07299   0.06763  -0.0667   0.0046   1.0000
  16.750   1.6943   0.07734   0.07208  -0.0672   0.0045   1.0000
  17.000   1.6848   0.08196   0.07680  -0.0679   0.0043   1.0000
  17.250   1.6758   0.08657   0.08152  -0.0687   0.0043   1.0000
  17.500   1.6666   0.09125   0.08630  -0.0695   0.0042   1.0000
  17.750   1.6569   0.09606   0.09122  -0.0705   0.0041   1.0000
  18.000   1.6469   0.10103   0.09629  -0.0717   0.0041   1.0000
  18.250   1.6362   0.10616   0.10154  -0.0730   0.0040   1.0000
  18.500   1.6253   0.11136   0.10684  -0.0745   0.0039   1.0000
  18.750   1.6143   0.11664   0.11222  -0.0761   0.0039   1.0000
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