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GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 406 AIRFOIL (goe406-il)
Reynolds number: 100,000
Max Cl/Cd: 54.15 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe406-il-100000.txt
Download as CSV file: xf-goe406-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 406 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  -0.2930   0.11585   0.11136  -0.0276   1.0000   0.0699
  -8.750  -0.3090   0.11557   0.11117  -0.0243   1.0000   0.0704
  -8.500  -0.3230   0.11500   0.11069  -0.0217   1.0000   0.0709
  -8.250  -0.3089   0.11172   0.10739  -0.0264   0.9952   0.0730
  -8.000  -0.2986   0.10902   0.10470  -0.0336   0.9874   0.0753
  -7.750  -0.3063   0.10820   0.10388  -0.0430   0.9751   0.0763
  -7.500  -0.2996   0.10513   0.10077  -0.0517   0.9637   0.0767
  -7.250  -0.2635   0.09812   0.09380  -0.0458   0.9658   0.0790
  -7.000  -0.2448   0.09469   0.09036  -0.0483   0.9598   0.0814
  -6.750  -0.2375   0.09204   0.08771  -0.0506   0.9509   0.0834
  -6.500  -0.2201   0.08875   0.08435  -0.0594   0.9428   0.0877
  -6.250  -0.2183   0.08797   0.08327  -0.0688   0.9284   0.0893
  -6.000  -0.2100   0.08279   0.07826  -0.0653   0.9228   0.0903
  -5.750  -0.1943   0.07926   0.07477  -0.0643   0.9175   0.0919
  -5.500  -0.1699   0.07581   0.07130  -0.0668   0.9134   0.0951
  -5.250  -0.1679   0.07393   0.06938  -0.0660   0.9037   0.0978
  -5.000  -0.1523   0.07344   0.06837  -0.0725   0.8942   0.1038
  -4.750  -0.1432   0.06888   0.06399  -0.0708   0.8882   0.1050
  -4.500  -0.1207   0.06540   0.06056  -0.0713   0.8842   0.1078
  -4.250  -0.1124   0.06363   0.05875  -0.0700   0.8768   0.1117
  -4.000  -0.0926   0.06193   0.05667  -0.0725   0.8695   0.1204
  -3.750  -0.0649   0.05810   0.05295  -0.0737   0.8667   0.1246
  -3.500  -0.0660   0.05716   0.05196  -0.0701   0.8563   0.1290
  -3.250  -0.0325   0.05412   0.04866  -0.0730   0.8516   0.1387
  -3.000  -0.0230   0.05246   0.04699  -0.0706   0.8411   0.1440
  -2.750   0.0179   0.04914   0.04345  -0.0736   0.8357   0.1576
  -2.500   0.0301   0.04795   0.04204  -0.0715   0.8246   0.1710
  -2.250   0.0681   0.04482   0.03883  -0.0735   0.8199   0.1894
  -2.000   0.1108   0.04214   0.03599  -0.0762   0.8174   0.2228
  -1.750   0.1036   0.04155   0.03547  -0.0705   0.8051   0.2283
  -0.250   0.3262   0.03082   0.02221  -0.0729   0.7692   0.1164
   0.000   0.3833   0.02867   0.01954  -0.0764   0.7658   0.1050
   0.250   0.3946   0.02852   0.01926  -0.0728   0.7543   0.1044
   0.500   0.4501   0.02688   0.01740  -0.0767   0.7494   0.1032
   0.750   0.4737   0.02623   0.01669  -0.0754   0.7390   0.1028
   1.000   0.5265   0.02480   0.01515  -0.0790   0.7322   0.1036
   1.250   0.5552   0.02400   0.01445  -0.0789   0.7213   0.1070
   1.500   0.6055   0.02287   0.01329  -0.0822   0.7137   0.1180
   1.750   0.6393   0.02235   0.01281  -0.0831   0.7009   0.1302
   2.000   0.8520   0.01898   0.01089  -0.1208   0.6834   1.0000
   2.250   0.8751   0.01896   0.01074  -0.1193   0.6691   1.0000
   2.500   0.8991   0.01890   0.01055  -0.1180   0.6543   1.0000
   2.750   0.9225   0.01884   0.01035  -0.1166   0.6381   1.0000
   3.000   0.9446   0.01882   0.01020  -0.1149   0.6207   1.0000
   3.250   0.9660   0.01884   0.01009  -0.1132   0.6022   1.0000
   3.500   0.9876   0.01891   0.01003  -0.1115   0.5838   1.0000
   3.750   1.0091   0.01906   0.01002  -0.1100   0.5659   1.0000
   4.000   1.0304   0.01929   0.01011  -0.1085   0.5490   1.0000
   4.250   1.0515   0.01958   0.01029  -0.1070   0.5334   1.0000
   4.500   1.0727   0.01993   0.01052  -0.1056   0.5194   1.0000
   4.750   1.0953   0.02030   0.01076  -0.1045   0.5072   1.0000
   5.000   1.1192   0.02067   0.01100  -0.1038   0.4963   1.0000
   5.250   1.1384   0.02119   0.01152  -0.1022   0.4854   1.0000
   5.500   1.1640   0.02165   0.01186  -0.1018   0.4773   1.0000
   5.750   1.1837   0.02222   0.01246  -0.1004   0.4687   1.0000
   6.000   1.2119   0.02273   0.01285  -0.1006   0.4622   1.0000
   6.250   1.2284   0.02340   0.01364  -0.0987   0.4549   1.0000
   6.500   1.2542   0.02393   0.01411  -0.0985   0.4486   1.0000
   6.750   1.2750   0.02462   0.01487  -0.0974   0.4428   1.0000
   7.000   1.2936   0.02533   0.01567  -0.0960   0.4370   1.0000
   7.250   1.3199   0.02596   0.01628  -0.0959   0.4323   1.0000
   7.500   1.3425   0.02677   0.01714  -0.0953   0.4280   1.0000
   7.750   1.3566   0.02767   0.01825  -0.0931   0.4235   1.0000
   8.000   1.3762   0.02849   0.01917  -0.0920   0.4192   1.0000
   8.250   1.4035   0.02919   0.01987  -0.0922   0.4152   1.0000
   8.500   1.4206   0.03019   0.02101  -0.0907   0.4112   1.0000
   8.750   1.4306   0.03132   0.02238  -0.0880   0.4074   1.0000
   9.000   1.4471   0.03221   0.02340  -0.0864   0.4028   1.0000
   9.250   1.4810   0.03266   0.02374  -0.0876   0.3967   1.0000
   9.500   1.4789   0.03378   0.02515  -0.0828   0.3908   1.0000
   9.750   1.5139   0.03367   0.02488  -0.0839   0.3810   1.0000
  10.000   1.5105   0.03469   0.02618  -0.0789   0.3743   1.0000
  10.250   1.5441   0.03456   0.02589  -0.0797   0.3646   1.0000
  10.500   1.5399   0.03561   0.02722  -0.0747   0.3585   1.0000
  10.750   1.5615   0.03570   0.02729  -0.0736   0.3497   1.0000
  11.000   1.5652   0.03646   0.02821  -0.0699   0.3426   1.0000
  11.250   1.5759   0.03683   0.02866  -0.0671   0.3349   1.0000
  11.500   1.5874   0.03728   0.02918  -0.0646   0.3273   1.0000
  11.750   1.5851   0.03784   0.02991  -0.0598   0.3199   1.0000
  12.000   1.5929   0.03792   0.02999  -0.0565   0.3111   1.0000
  12.250   1.5809   0.03858   0.03082  -0.0504   0.3042   1.0000
  12.500   1.5848   0.03865   0.03091  -0.0468   0.2951   1.0000
  12.750   1.5705   0.03962   0.03208  -0.0412   0.2876   1.0000
  13.000   1.5661   0.04016   0.03269  -0.0371   0.2785   1.0000
  13.250   1.5522   0.04139   0.03410  -0.0326   0.2694   1.0000
  13.500   1.5351   0.04315   0.03604  -0.0285   0.2596   1.0000
  13.750   1.5191   0.04509   0.03809  -0.0251   0.2477   1.0000
  14.000   1.4979   0.04799   0.04115  -0.0223   0.2335   1.0000
  14.250   1.4739   0.05186   0.04522  -0.0203   0.2153   1.0000
  14.500   1.4490   0.05637   0.04976  -0.0190   0.1918   1.0000
  14.750   1.4190   0.06200   0.05527  -0.0184   0.1608   1.0000
  15.000   1.3891   0.06818   0.06130  -0.0183   0.1434   1.0000
  15.250   1.3588   0.07495   0.06798  -0.0189   0.1323   1.0000
  15.500   1.3294   0.08201   0.07498  -0.0199   0.1239   1.0000
  15.750   1.3012   0.08916   0.08204  -0.0212   0.1162   1.0000
  16.000   1.2815   0.09522   0.08808  -0.0222   0.1086   1.0000
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