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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 500,000
Max Cl/Cd: 104.27 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe401-il-500000.txt
Download as CSV file: xf-goe401-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3376   0.09792   0.09564  -0.0228   1.0000   0.0221
  -8.250  -0.3417   0.09553   0.09329  -0.0237   1.0000   0.0222
  -8.000  -0.3456   0.09318   0.09098  -0.0237   1.0000   0.0222
  -7.750  -0.3450   0.08930   0.08714  -0.0228   1.0000   0.0224
  -7.500  -0.3368   0.08638   0.08423  -0.0207   1.0000   0.0226
  -7.250  -0.3332   0.08400   0.08189  -0.0201   1.0000   0.0229
  -7.000  -0.3303   0.08163   0.07955  -0.0201   1.0000   0.0231
  -6.750  -0.3283   0.07941   0.07736  -0.0200   1.0000   0.0233
  -6.500  -0.3063   0.07580   0.07375  -0.0251   0.9975   0.0240
  -6.250  -0.2743   0.07133   0.06925  -0.0330   0.9924   0.0250
  -6.000  -0.1650   0.04656   0.04444  -0.0562   0.9530   0.0274
  -5.750  -0.1398   0.04225   0.04011  -0.0594   0.9435   0.0278
  -5.500  -0.1080   0.03838   0.03619  -0.0640   0.9315   0.0284
  -5.250  -0.0734   0.03439   0.03211  -0.0699   0.9164   0.0293
  -5.000  -0.0439   0.03078   0.02835  -0.0746   0.8960   0.0309
  -4.750  -0.0085   0.02706   0.02430  -0.0805   0.8764   0.0332
  -4.500   0.0085   0.02227   0.01930  -0.0824   0.8597   0.0337
  -4.250   0.0252   0.02009   0.01702  -0.0822   0.8432   0.0342
  -4.000   0.0443   0.01843   0.01528  -0.0822   0.8282   0.0348
  -3.750   0.0651   0.01680   0.01353  -0.0822   0.8142   0.0357
  -3.500   0.0873   0.01517   0.01176  -0.0825   0.8006   0.0371
  -3.250   0.1199   0.01376   0.00998  -0.0830   0.7884   0.0410
  -3.000   0.1376   0.01060   0.00662  -0.0833   0.7765   0.0423
  -2.750   0.1593   0.00969   0.00562  -0.0830   0.7628   0.0432
  -2.500   0.1821   0.00889   0.00471  -0.0827   0.7490   0.0447
  -2.250   0.2204   0.02225   0.01766  -0.0881   0.7599   0.0477
  -2.000   0.2448   0.01999   0.01505  -0.0871   0.7457   0.0523
  -1.750   0.2682   0.01930   0.01428  -0.0865   0.7302   0.0538
  -1.500   0.2924   0.01863   0.01347  -0.0858   0.7139   0.0568
  -1.250   0.3171   0.01729   0.01181  -0.0847   0.6975   0.0639
  -1.000   0.3410   0.01669   0.01114  -0.0840   0.6787   0.0659
  -0.750   0.3673   0.01223   0.00568  -0.0815   0.6635   0.0417
  -0.500   0.3926   0.01200   0.00530  -0.0806   0.6398   0.0412
  -0.250   0.4169   0.01124   0.00435  -0.0796   0.6141   0.0408
   0.000   0.4410   0.01083   0.00375  -0.0786   0.5844   0.0407
   0.250   0.4651   0.01067   0.00342  -0.0776   0.5528   0.0409
   0.500   0.4886   0.01038   0.00296  -0.0766   0.5243   0.0416
   0.750   0.5125   0.01019   0.00265  -0.0756   0.5011   0.0418
   1.000   0.5367   0.01005   0.00241  -0.0747   0.4839   0.0424
   1.250   0.5614   0.00996   0.00225  -0.0739   0.4703   0.0437
   1.500   0.5865   0.00994   0.00218  -0.0732   0.4590   0.0454
   1.750   0.6117   0.00998   0.00216  -0.0725   0.4494   0.0476
   2.000   0.6376   0.01000   0.00215  -0.0720   0.4406   0.0503
   2.250   0.6628   0.01002   0.00220  -0.0713   0.4329   0.0671
   2.500   0.6883   0.00996   0.00234  -0.0708   0.4253   0.1423
   2.750   0.7134   0.01006   0.00245  -0.0702   0.4185   0.1809
   3.000   0.7341   0.00937   0.00260  -0.0690   0.4123   0.5622
   3.250   0.8089   0.00875   0.00280  -0.0797   0.4021   1.0000
   3.500   0.8344   0.00886   0.00290  -0.0791   0.3958   1.0000
   3.750   0.8589   0.00905   0.00301  -0.0783   0.3885   1.0000
   4.000   0.8843   0.00915   0.00312  -0.0777   0.3806   1.0000
   4.250   0.9088   0.00933   0.00324  -0.0770   0.3734   1.0000
   4.500   0.9340   0.00946   0.00337  -0.0763   0.3670   1.0000
   4.750   0.9587   0.00961   0.00350  -0.0757   0.3595   1.0000
   5.000   0.9836   0.00975   0.00364  -0.0750   0.3511   1.0000
   5.250   1.0079   0.00993   0.00378  -0.0742   0.3426   1.0000
   5.500   1.0328   0.01006   0.00393  -0.0736   0.3343   1.0000
   6.000   1.0816   0.01041   0.00429  -0.0722   0.3179   1.0000
   6.250   1.1055   0.01062   0.00448  -0.0714   0.3088   1.0000
   6.500   1.1292   0.01083   0.00467  -0.0706   0.2971   1.0000
   6.750   1.1526   0.01106   0.00487  -0.0698   0.2827   1.0000
   7.000   1.1756   0.01133   0.00510  -0.0689   0.2674   1.0000
   7.250   1.1984   0.01162   0.00536  -0.0680   0.2535   1.0000
   7.500   1.2206   0.01196   0.00566  -0.0671   0.2377   1.0000
   7.750   1.2426   0.01232   0.00599  -0.0661   0.2200   1.0000
   8.000   1.2637   0.01274   0.00635  -0.0650   0.2003   1.0000
   8.250   1.2829   0.01333   0.00680  -0.0636   0.1716   1.0000
   8.500   1.2968   0.01439   0.00753  -0.0615   0.1172   1.0000
   8.750   1.3052   0.01590   0.00868  -0.0587   0.0645   1.0000
   9.000   1.3215   0.01669   0.00945  -0.0569   0.0536   1.0000
   9.250   1.3374   0.01748   0.01023  -0.0551   0.0436   1.0000
   9.500   1.3535   0.01822   0.01096  -0.0533   0.0333   1.0000
   9.750   1.3674   0.01908   0.01179  -0.0511   0.0274   1.0000
  10.000   1.3826   0.01978   0.01255  -0.0492   0.0245   1.0000
  10.250   1.3924   0.02079   0.01360  -0.0465   0.0221   1.0000
  10.500   1.4040   0.02151   0.01440  -0.0441   0.0210   1.0000
  10.750   1.4125   0.02231   0.01527  -0.0411   0.0199   1.0000
  11.000   1.4191   0.02324   0.01628  -0.0381   0.0190   1.0000
  11.250   1.4230   0.02438   0.01749  -0.0350   0.0184   1.0000
  11.500   1.4183   0.02612   0.01934  -0.0313   0.0176   1.0000
  11.750   1.4163   0.02789   0.02123  -0.0285   0.0172   1.0000
  12.000   1.4210   0.02935   0.02279  -0.0267   0.0168   1.0000
  12.250   1.4219   0.03125   0.02481  -0.0251   0.0164   1.0000
  12.500   1.4223   0.03337   0.02704  -0.0238   0.0161   1.0000
  12.750   1.4234   0.03559   0.02936  -0.0229   0.0156   1.0000
  13.000   1.4224   0.03818   0.03204  -0.0222   0.0153   1.0000
  13.250   1.4212   0.04094   0.03490  -0.0219   0.0149   1.0000
  13.500   1.4181   0.04404   0.03809  -0.0218   0.0146   1.0000
  13.750   1.4133   0.04745   0.04159  -0.0220   0.0143   1.0000
  14.000   1.4083   0.05095   0.04519  -0.0221   0.0142   1.0000
  14.250   1.4011   0.05476   0.04910  -0.0224   0.0140   1.0000
  14.500   1.3890   0.05900   0.05343  -0.0223   0.0136   1.0000
  14.750   1.3844   0.06249   0.05702  -0.0223   0.0135   1.0000
  15.000   1.3830   0.06584   0.06048  -0.0229   0.0134   1.0000
  15.250   1.3809   0.06936   0.06412  -0.0236   0.0132   1.0000
  15.500   1.3785   0.07295   0.06783  -0.0243   0.0131   1.0000
  15.750   1.3760   0.07664   0.07164  -0.0251   0.0129   1.0000
  16.000   1.3722   0.08047   0.07558  -0.0258   0.0127   1.0000
  16.250   1.3692   0.08425   0.07949  -0.0267   0.0127   1.0000
  16.500   1.3652   0.08832   0.08368  -0.0278   0.0125   1.0000
  16.750   1.3604   0.09259   0.08807  -0.0291   0.0123   1.0000
  17.000   1.3555   0.09692   0.09252  -0.0305   0.0121   1.0000
  17.250   1.3496   0.10152   0.09724  -0.0321   0.0120   1.0000
  17.500   1.3445   0.10612   0.10195  -0.0340   0.0118   1.0000
  17.750   1.3379   0.11099   0.10694  -0.0360   0.0117   1.0000
  18.000   1.3314   0.11596   0.11203  -0.0382   0.0116   1.0000
  18.250   1.3213   0.12170   0.11793  -0.0408   0.0116   1.0000
  18.500   1.3161   0.12672   0.12302  -0.0435   0.0113   1.0000
  18.750   1.3076   0.13242   0.12885  -0.0465   0.0112   1.0000
  19.000   1.3009   0.13784   0.13436  -0.0495   0.0111   1.0000
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