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GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 407 AIRFOIL (goe407-il)
Reynolds number: 500,000
Max Cl/Cd: 106.47 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe407-il-500000.txt
Download as CSV file: xf-goe407-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 407 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3257   0.10225   0.10001  -0.0259   1.0000   0.0233
  -8.750  -0.3264   0.09983   0.09761  -0.0256   1.0000   0.0238
  -8.500  -0.3285   0.09742   0.09524  -0.0252   1.0000   0.0244
  -8.250  -0.3249   0.09351   0.09134  -0.0312   0.9980   0.0256
  -8.000  -0.3131   0.08844   0.08626  -0.0419   0.9928   0.0258
  -7.750  -0.2939   0.08235   0.08015  -0.0510   0.9869   0.0259
  -7.500  -0.2766   0.07888   0.07668  -0.0510   0.9852   0.0262
  -7.250  -0.2516   0.07540   0.07319  -0.0548   0.9833   0.0266
  -7.000  -0.2337   0.07199   0.06977  -0.0583   0.9768   0.0270
  -6.750  -0.2077   0.06800   0.06575  -0.0643   0.9730   0.0277
  -6.500  -0.1843   0.06401   0.06172  -0.0697   0.9673   0.0285
  -6.250  -0.1484   0.05771   0.05524  -0.0810   0.9596   0.0307
  -6.000  -0.1267   0.05169   0.04905  -0.0859   0.9508   0.0311
  -5.750  -0.1055   0.04861   0.04595  -0.0875   0.9452   0.0315
  -5.500  -0.0867   0.04633   0.04365  -0.0880   0.9345   0.0319
  -5.250  -0.0637   0.04388   0.04113  -0.0893   0.9222   0.0324
  -5.000  -0.0345   0.04107   0.03821  -0.0919   0.9081   0.0334
  -4.750   0.0113   0.03659   0.03326  -0.0968   0.8911   0.0369
  -4.500   0.0424   0.03188   0.02832  -0.1006   0.8710   0.0377
  -4.250   0.0750   0.03019   0.02644  -0.1030   0.8459   0.0384
  -3.750   0.1185   0.02755   0.02334  -0.1018   0.8008   0.0410
  -3.500   0.1335   0.02458   0.01983  -0.0987   0.7843   0.0450
  -3.250   0.1521   0.02352   0.01868  -0.0974   0.7693   0.0458
  -2.750   0.1919   0.02175   0.01668  -0.0946   0.7447   0.0489
  -2.500   0.2105   0.02015   0.01465  -0.0921   0.7348   0.0541
  -2.250   0.2316   0.01925   0.01370  -0.0910   0.7249   0.0552
  -2.000   0.2535   0.01855   0.01294  -0.0899   0.7156   0.0571
  -1.750   0.2811   0.01979   0.01385  -0.0886   0.7071   0.0628
  -1.500   0.2973   0.01688   0.01088  -0.0870   0.6988   0.0658
  -1.250   0.3204   0.01626   0.01017  -0.0860   0.6909   0.0682
  -1.000   0.3469   0.01251   0.00565  -0.0834   0.6840   0.0415
  -0.750   0.3725   0.01184   0.00483  -0.0826   0.6765   0.0408
  -0.500   0.3980   0.01133   0.00426  -0.0819   0.6692   0.0407
  -0.250   0.4231   0.01097   0.00381  -0.0811   0.6620   0.0408
   0.000   0.4479   0.01072   0.00354  -0.0803   0.6549   0.0417
   0.250   0.4723   0.01049   0.00327  -0.0794   0.6476   0.0425
   0.500   0.4967   0.01028   0.00302  -0.0785   0.6413   0.0428
   0.750   0.5207   0.01009   0.00283  -0.0775   0.6342   0.0435
   1.250   0.5683   0.00980   0.00250  -0.0755   0.6196   0.0460
   1.500   0.5925   0.00976   0.00243  -0.0746   0.6120   0.0485
   1.750   0.6167   0.00970   0.00239  -0.0736   0.6039   0.0524
   2.000   0.6405   0.00966   0.00237  -0.0726   0.5958   0.0669
   2.250   0.6606   0.00918   0.00245  -0.0711   0.5870   0.2840
   2.500   0.8569   0.00827   0.00300  -0.1095   0.5587   1.0000
   2.750   0.8793   0.00837   0.00303  -0.1083   0.5423   1.0000
   3.000   0.9012   0.00849   0.00308  -0.1070   0.5217   1.0000
   3.250   0.9220   0.00866   0.00313  -0.1054   0.4978   1.0000
   3.750   0.9615   0.00919   0.00337  -0.1020   0.4438   1.0000
   4.000   0.9815   0.00947   0.00354  -0.1005   0.4239   1.0000
   4.250   1.0019   0.00975   0.00372  -0.0989   0.4071   1.0000
   4.500   1.0227   0.01001   0.00390  -0.0975   0.3919   1.0000
   4.750   1.0437   0.01025   0.00409  -0.0961   0.3785   1.0000
   5.000   1.0649   0.01048   0.00429  -0.0948   0.3674   1.0000
   5.250   1.0854   0.01074   0.00450  -0.0933   0.3572   1.0000
   5.500   1.1067   0.01096   0.00469  -0.0920   0.3470   1.0000
   5.750   1.1274   0.01119   0.00491  -0.0906   0.3372   1.0000
   6.000   1.1473   0.01146   0.00514  -0.0891   0.3276   1.0000
   6.250   1.1686   0.01166   0.00536  -0.0878   0.3194   1.0000
   6.500   1.1878   0.01196   0.00561  -0.0861   0.3107   1.0000
   6.750   1.2088   0.01215   0.00584  -0.0848   0.3024   1.0000
   7.000   1.2278   0.01243   0.00610  -0.0831   0.2942   1.0000
   7.250   1.2471   0.01268   0.00634  -0.0815   0.2828   1.0000
   7.500   1.2662   0.01294   0.00659  -0.0799   0.2718   1.0000
   7.750   1.2840   0.01324   0.00688  -0.0780   0.2601   1.0000
   8.000   1.3009   0.01357   0.00718  -0.0760   0.2487   1.0000
   8.250   1.3175   0.01390   0.00749  -0.0739   0.2353   1.0000
   8.500   1.3323   0.01430   0.00783  -0.0715   0.2162   1.0000
   8.750   1.3427   0.01480   0.00823  -0.0683   0.1922   1.0000
   9.000   1.3460   0.01553   0.00875  -0.0638   0.1540   1.0000
   9.250   1.3492   0.01631   0.00937  -0.0594   0.1316   1.0000
   9.500   1.3564   0.01696   0.00998  -0.0558   0.1213   1.0000
   9.750   1.3656   0.01756   0.01057  -0.0527   0.1142   1.0000
  10.000   1.3748   0.01818   0.01121  -0.0496   0.1077   1.0000
  10.250   1.3870   0.01868   0.01176  -0.0471   0.1033   1.0000
  10.500   1.3955   0.01939   0.01246  -0.0441   0.0972   1.0000
  10.750   1.4084   0.01990   0.01303  -0.0419   0.0923   1.0000
  11.000   1.4198   0.02051   0.01367  -0.0395   0.0866   1.0000
  11.250   1.4304   0.02119   0.01437  -0.0372   0.0803   1.0000
  11.500   1.4395   0.02198   0.01514  -0.0347   0.0703   1.0000
  11.750   1.4422   0.02320   0.01622  -0.0316   0.0512   1.0000
  12.000   1.4367   0.02501   0.01788  -0.0278   0.0322   1.0000
  12.250   1.4368   0.02658   0.01945  -0.0250   0.0265   1.0000
  12.500   1.4378   0.02821   0.02111  -0.0225   0.0238   1.0000
  12.750   1.4407   0.02979   0.02279  -0.0204   0.0223   1.0000
  13.000   1.4414   0.03165   0.02472  -0.0184   0.0211   1.0000
  13.250   1.4395   0.03383   0.02698  -0.0166   0.0200   1.0000
  13.500   1.4384   0.03607   0.02932  -0.0150   0.0195   1.0000
  13.750   1.4398   0.03816   0.03152  -0.0138   0.0189   1.0000
  14.000   1.4385   0.04060   0.03407  -0.0127   0.0184   1.0000
  14.250   1.4364   0.04324   0.03680  -0.0118   0.0179   1.0000
  14.500   1.4340   0.04597   0.03964  -0.0111   0.0175   1.0000
  14.750   1.4273   0.04931   0.04307  -0.0106   0.0169   1.0000
  15.000   1.4208   0.05271   0.04658  -0.0103   0.0167   1.0000
  15.250   1.4091   0.05685   0.05082  -0.0101   0.0164   1.0000
  15.500   1.3958   0.06134   0.05542  -0.0103   0.0161   1.0000
  15.750   1.3881   0.06528   0.05946  -0.0106   0.0159   1.0000
  16.000   1.3830   0.06898   0.06327  -0.0110   0.0157   1.0000
  16.250   1.3760   0.07305   0.06745  -0.0115   0.0156   1.0000
  16.500   1.3693   0.07719   0.07169  -0.0122   0.0154   1.0000
  16.750   1.3633   0.08128   0.07589  -0.0131   0.0151   1.0000
  17.000   1.3569   0.08548   0.08019  -0.0140   0.0149   1.0000
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