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GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 407 AIRFOIL (goe407-il)
Reynolds number: 200,000
Max Cl/Cd: 79.38 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe407-il-200000.txt
Download as CSV file: xf-goe407-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2500   0.09608   0.09288  -0.0297   1.0000   0.0434
  -8.500  -0.2649   0.09467   0.09154  -0.0298   1.0000   0.0438
  -8.250  -0.2845   0.09377   0.09074  -0.0288   1.0000   0.0440
  -8.000  -0.2916   0.09106   0.08807  -0.0329   0.9966   0.0441
  -7.750  -0.2689   0.08468   0.08169  -0.0334   0.9946   0.0447
  -7.500  -0.2449   0.08007   0.07707  -0.0343   0.9915   0.0457
  -7.250  -0.2277   0.07576   0.07275  -0.0380   0.9866   0.0469
  -7.000  -0.3376   0.08551   0.08234  -0.0352   0.9904   0.0448
  -6.750  -0.3141   0.08168   0.07850  -0.0369   0.9862   0.0457
  -6.500  -0.2873   0.07768   0.07447  -0.0419   0.9802   0.0471
  -6.250  -0.2580   0.07348   0.07021  -0.0488   0.9730   0.0497
  -6.000  -0.2152   0.06760   0.06399  -0.0655   0.9599   0.0530
  -5.750  -0.1927   0.06323   0.05969  -0.0666   0.9571   0.0538
  -5.500  -0.1734   0.06023   0.05671  -0.0674   0.9472   0.0549
  -5.250  -0.1409   0.05675   0.05315  -0.0717   0.9430   0.0571
  -5.000  -0.0994   0.05443   0.05027  -0.0787   0.9300   0.0627
  -4.750  -0.0816   0.04929   0.04515  -0.0799   0.9211   0.0637
  -4.500  -0.0560   0.04614   0.04208  -0.0814   0.9158   0.0653
  -4.250   0.0263   0.02713   0.02269  -0.0885   0.8889   0.0748
  -4.000   0.0492   0.02252   0.01821  -0.0904   0.8843   0.0763
  -3.750   0.0346   0.03773   0.03304  -0.0872   0.8916   0.0763
  -3.500   0.0664   0.03519   0.03048  -0.0893   0.8854   0.0786
  -3.250   0.1040   0.03561   0.03026  -0.0900   0.8750   0.0877
  -3.000   0.1340   0.03056   0.02529  -0.0927   0.8679   0.0903
  -2.750   0.1635   0.02872   0.02337  -0.0936   0.8550   0.0939
  -2.500   0.1925   0.02721   0.02150  -0.0938   0.8419   0.1048
  -2.250   0.2204   0.02576   0.01998  -0.0942   0.8303   0.1102
  -2.000   0.2485   0.02446   0.01838  -0.0943   0.8200   0.1212
  -1.750   0.2713   0.02380   0.01748  -0.0931   0.8085   0.1348
  -1.500   0.2945   0.02246   0.01612  -0.0925   0.7983   0.1407
  -1.250   0.3289   0.01909   0.01168  -0.0901   0.7903   0.0771
  -1.000   0.3545   0.01780   0.01017  -0.0889   0.7807   0.0688
  -0.750   0.3838   0.01695   0.00907  -0.0887   0.7726   0.0683
  -0.500   0.4081   0.01620   0.00816  -0.0875   0.7628   0.0672
  -0.250   0.4374   0.01550   0.00724  -0.0873   0.7548   0.0658
   0.000   0.4622   0.01498   0.00668  -0.0863   0.7450   0.0659
   0.250   0.4890   0.01453   0.00619  -0.0858   0.7367   0.0670
   0.500   0.5138   0.01416   0.00581  -0.0849   0.7274   0.0685
   0.750   0.5382   0.01388   0.00551  -0.0839   0.7185   0.0713
   1.000   0.5629   0.01362   0.00522  -0.0829   0.7096   0.0759
   1.250   0.5848   0.01335   0.00500  -0.0815   0.7000   0.0825
   1.500   0.7549   0.01104   0.00468  -0.1129   0.6850   1.0000
   1.750   0.7795   0.01115   0.00464  -0.1120   0.6753   1.0000
   2.000   0.8016   0.01127   0.00470  -0.1107   0.6637   1.0000
   2.250   0.8245   0.01140   0.00475  -0.1095   0.6522   1.0000
   2.500   0.8477   0.01154   0.00478  -0.1083   0.6405   1.0000
   2.750   0.8705   0.01168   0.00483  -0.1071   0.6279   1.0000
   3.000   0.8918   0.01181   0.00494  -0.1055   0.6138   1.0000
   3.250   0.9129   0.01195   0.00502  -0.1040   0.5986   1.0000
   3.500   0.9337   0.01209   0.00510  -0.1023   0.5822   1.0000
   3.750   0.9541   0.01224   0.00518  -0.1006   0.5649   1.0000
   4.000   0.9741   0.01239   0.00528  -0.0988   0.5467   1.0000
   4.250   0.9934   0.01255   0.00540  -0.0969   0.5260   1.0000
   4.500   1.0121   0.01275   0.00551  -0.0949   0.5044   1.0000
   4.750   1.0306   0.01302   0.00564  -0.0930   0.4842   1.0000
   5.000   1.0495   0.01332   0.00586  -0.0911   0.4653   1.0000
   5.250   1.0688   0.01367   0.00611  -0.0894   0.4492   1.0000
   5.500   1.0884   0.01406   0.00640  -0.0877   0.4352   1.0000
   5.750   1.1081   0.01446   0.00673  -0.0861   0.4221   1.0000
   6.000   1.1279   0.01482   0.00707  -0.0846   0.4095   1.0000
   6.250   1.1476   0.01519   0.00743  -0.0830   0.3980   1.0000
   6.500   1.1679   0.01562   0.00779  -0.0816   0.3884   1.0000
   6.750   1.1872   0.01596   0.00818  -0.0800   0.3780   1.0000
   7.000   1.2066   0.01634   0.00857  -0.0785   0.3685   1.0000
   7.250   1.2254   0.01675   0.00893  -0.0768   0.3589   1.0000
   7.500   1.2438   0.01706   0.00934  -0.0750   0.3496   1.0000
   7.750   1.2621   0.01748   0.00974  -0.0733   0.3408   1.0000
   8.000   1.2790   0.01779   0.01015  -0.0713   0.3314   1.0000
   8.250   1.2958   0.01817   0.01056  -0.0693   0.3223   1.0000
   8.500   1.3109   0.01855   0.01096  -0.0669   0.3122   1.0000
   8.750   1.3243   0.01887   0.01139  -0.0643   0.3004   1.0000
   9.000   1.3357   0.01924   0.01181  -0.0613   0.2871   1.0000
   9.250   1.3441   0.01962   0.01222  -0.0577   0.2726   1.0000
   9.500   1.3502   0.02002   0.01264  -0.0538   0.2575   1.0000
   9.750   1.3552   0.02051   0.01313  -0.0498   0.2395   1.0000
  10.000   1.3585   0.02117   0.01373  -0.0457   0.2196   1.0000
  10.250   1.3631   0.02193   0.01447  -0.0421   0.1952   1.0000
  10.500   1.3658   0.02289   0.01534  -0.0384   0.1731   1.0000
  10.750   1.3684   0.02397   0.01633  -0.0349   0.1559   1.0000
  11.000   1.3707   0.02516   0.01746  -0.0316   0.1443   1.0000
  11.250   1.3713   0.02651   0.01875  -0.0284   0.1353   1.0000
  11.500   1.3753   0.02777   0.02006  -0.0258   0.1273   1.0000
  11.750   1.3760   0.02930   0.02160  -0.0230   0.1210   1.0000
  12.000   1.3812   0.03063   0.02304  -0.0209   0.1144   1.0000
  12.250   1.3794   0.03254   0.02491  -0.0185   0.1086   1.0000
  12.500   1.3870   0.03383   0.02639  -0.0170   0.1016   1.0000
  12.750   1.3863   0.03583   0.02842  -0.0152   0.0937   1.0000
  13.000   1.3878   0.03778   0.03044  -0.0138   0.0828   1.0000
  13.250   1.3902   0.03980   0.03250  -0.0127   0.0657   1.0000
  13.500   1.3824   0.04286   0.03551  -0.0114   0.0540   1.0000
  13.750   1.3741   0.04611   0.03878  -0.0102   0.0480   1.0000
  14.000   1.3657   0.04950   0.04220  -0.0095   0.0440   1.0000
  14.250   1.3575   0.05302   0.04578  -0.0089   0.0413   1.0000
  14.500   1.3525   0.05625   0.04913  -0.0084   0.0395   1.0000
  14.750   1.3452   0.05988   0.05282  -0.0083   0.0373   1.0000
  15.000   1.3365   0.06373   0.05674  -0.0083   0.0362   1.0000
  15.250   1.3285   0.06762   0.06071  -0.0084   0.0348   1.0000
  15.500   1.3244   0.07113   0.06435  -0.0085   0.0336   1.0000
  15.750   1.3202   0.07472   0.06804  -0.0088   0.0327   1.0000
  16.000   1.3160   0.07832   0.07174  -0.0091   0.0319   1.0000
  16.250   1.3111   0.08206   0.07555  -0.0096   0.0310   1.0000
  16.500   1.3073   0.08562   0.07914  -0.0099   0.0302   1.0000
  16.750   1.3067   0.08833   0.08183  -0.0093   0.0294   1.0000
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