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FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FAUVEL 14% AIRFOIL (fauvel-il)
Reynolds number: 50,000
Max Cl/Cd: 18.3 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fauvel-il-50000-n5.txt
Download as CSV file: xf-fauvel-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FAUVEL 14% AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5369   0.11193   0.10534   0.0083   1.0000   0.0711
 -10.500  -0.5345   0.10731   0.10078   0.0062   1.0000   0.0709
 -10.250  -0.5356   0.10216   0.09570   0.0033   1.0000   0.0706
 -10.000  -0.5401   0.09641   0.09000  -0.0004   1.0000   0.0705
  -9.750  -0.5465   0.09036   0.08401  -0.0046   1.0000   0.0701
  -9.500  -0.5580   0.08434   0.07802  -0.0086   1.0000   0.0696
  -9.250  -0.5738   0.07881   0.07248  -0.0113   1.0000   0.0691
  -9.000  -0.5908   0.07403   0.06767  -0.0123   1.0000   0.0687
  -8.750  -0.6064   0.06975   0.06332  -0.0121   1.0000   0.0684
  -8.500  -0.6163   0.06549   0.05888  -0.0121   0.8869   0.0680
  -8.250  -0.6181   0.06119   0.05408  -0.0122   0.8344   0.0677
  -8.000  -0.6198   0.05761   0.05005  -0.0107   0.8094   0.0676
  -7.750  -0.6183   0.05432   0.04631  -0.0089   0.7915   0.0677
  -7.500  -0.6133   0.05133   0.04286  -0.0070   0.7767   0.0682
  -7.250  -0.6058   0.04860   0.03960  -0.0051   0.7638   0.0693
  -7.000  -0.5955   0.04599   0.03641  -0.0031   0.7515   0.0705
  -6.750  -0.5803   0.04372   0.03372  -0.0016   0.7397   0.0716
  -6.500  -0.5611   0.04189   0.03166  -0.0005   0.7286   0.0726
  -6.250  -0.5401   0.04008   0.02960   0.0005   0.7171   0.0736
  -6.000  -0.5183   0.03843   0.02766   0.0015   0.7068   0.0748
  -5.750  -0.4952   0.03697   0.02592   0.0024   0.6961   0.0768
  -5.500  -0.4706   0.03561   0.02422   0.0031   0.6860   0.0795
  -5.250  -0.4446   0.03431   0.02263   0.0038   0.6763   0.0819
  -5.000  -0.4167   0.03311   0.02138   0.0039   0.6659   0.0841
  -4.750  -0.3878   0.03207   0.02019   0.0042   0.6568   0.0868
  -4.500  -0.3565   0.03113   0.01912   0.0040   0.6463   0.0908
  -4.250  -0.3257   0.03027   0.01819   0.0040   0.6376   0.0958
  -4.000  -0.2939   0.02951   0.01739   0.0036   0.6271   0.1021
  -3.750  -0.2640   0.02877   0.01658   0.0037   0.6185   0.1086
  -3.500  -0.2368   0.02812   0.01591   0.0040   0.6092   0.1196
  -3.250  -0.2129   0.02739   0.01533   0.0048   0.6012   0.1364
  -3.000  -0.1915   0.02659   0.01488   0.0059   0.5924   0.1696
  -2.750  -0.1732   0.02579   0.01450   0.0074   0.5855   0.2545
  -2.500  -0.1595   0.02477   0.01410   0.0095   0.5772   0.3639
  -2.250  -0.0952   0.02504   0.01620   0.0091   0.5674   0.8269
  -2.000  -0.0151   0.02672   0.01745   0.0041   0.5564   0.9043
  -1.750   0.0379   0.02716   0.01762   0.0003   0.5463   0.9316
  -1.500   0.0771   0.02721   0.01737  -0.0016   0.5392   0.9453
  -1.250   0.1176   0.02731   0.01731  -0.0042   0.5300   0.9578
  -1.000   0.1595   0.02722   0.01698  -0.0069   0.5230   0.9692
  -0.750   0.2040   0.02720   0.01682  -0.0105   0.5144   0.9813
  -0.500   0.2523   0.02693   0.01635  -0.0146   0.5070   0.9946
  -0.250   0.2852   0.02691   0.01621  -0.0162   0.5004   1.0000
   0.000   0.3067   0.02710   0.01635  -0.0157   0.4938   1.0000
   0.250   0.3273   0.02714   0.01626  -0.0147   0.4890   1.0000
   0.500   0.3487   0.02741   0.01647  -0.0141   0.4829   1.0000
   0.750   0.3699   0.02769   0.01673  -0.0136   0.4766   1.0000
   1.000   0.3904   0.02780   0.01672  -0.0125   0.4722   1.0000
   1.250   0.4112   0.02807   0.01694  -0.0118   0.4674   1.0000
   1.500   0.4322   0.02862   0.01752  -0.0115   0.4607   1.0000
   1.750   0.4524   0.02884   0.01767  -0.0105   0.4561   1.0000
   2.000   0.4724   0.02892   0.01764  -0.0091   0.4526   1.0000
   2.250   0.4922   0.02983   0.01865  -0.0090   0.4458   1.0000
   2.500   0.5116   0.03035   0.01917  -0.0082   0.4408   1.0000
   2.750   0.5311   0.03060   0.01935  -0.0069   0.4370   1.0000
   3.000   0.5503   0.03102   0.01973  -0.0058   0.4330   1.0000
   3.250   0.5671   0.03226   0.02111  -0.0056   0.4261   1.0000
   3.500   0.5852   0.03283   0.02167  -0.0045   0.4217   1.0000
   3.750   0.6042   0.03313   0.02192  -0.0030   0.4185   1.0000
   4.000   0.6198   0.03425   0.02311  -0.0023   0.4133   1.0000
   4.250   0.6330   0.03565   0.02462  -0.0017   0.4070   1.0000
   4.500   0.6498   0.03626   0.02523  -0.0002   0.4030   1.0000
   4.750   0.6686   0.03654   0.02546   0.0014   0.4001   1.0000
   5.000   0.6737   0.03894   0.02803   0.0019   0.3931   1.0000
   5.250   0.6836   0.04037   0.02952   0.0031   0.3876   1.0000
   5.500   0.7002   0.04086   0.02999   0.0048   0.3840   1.0000
   5.750   0.7208   0.04091   0.03001   0.0066   0.3815   1.0000
   6.000   0.6991   0.04580   0.03511   0.0070   0.3713   1.0000
   6.250   0.7131   0.04650   0.03582   0.0088   0.3673   1.0000
   6.500   0.7352   0.04637   0.03566   0.0107   0.3646   1.0000
   7.000   0.7069   0.05349   0.04289   0.0127   0.3490   1.0000
   7.250   0.7355   0.05260   0.04198   0.0149   0.3467   1.0000
   7.750   0.6969   0.06037   0.04974   0.0165   0.3302   1.0000
   8.250   0.6702   0.06684   0.05618   0.0181   0.3144   1.0000
   8.750   0.6601   0.07249   0.06181   0.0188   0.2994   1.0000
   9.000   0.6896   0.07166   0.06101   0.0207   0.2962   1.0000
   9.250   0.6585   0.07765   0.06698   0.0192   0.2848   1.0000
   9.500   0.6816   0.07758   0.06694   0.0206   0.2809   1.0000
   9.750   0.6610   0.08270   0.07207   0.0193   0.2708   1.0000
  10.000   0.6778   0.08344   0.07285   0.0202   0.2661   1.0000
  10.500   0.6760   0.08939   0.07885   0.0196   0.2517   1.0000
  10.750   0.7023   0.08887   0.07837   0.0211   0.2486   1.0000
  11.000   0.6751   0.09562   0.08513   0.0186   0.2380   1.0000
  11.250   0.6959   0.09586   0.08540   0.0197   0.2343   1.0000
  11.500   0.6764   0.10180   0.09136   0.0174   0.2251   1.0000
  11.750   0.6907   0.10300   0.09262   0.0179   0.2206   1.0000
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