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FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 61-147 AIRFOIL (fx61147-il)
Reynolds number: 200,000
Max Cl/Cd: 70.81 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61147-il-200000.txt
Download as CSV file: xf-fx61147-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-147 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3865   0.08999   0.08681  -0.0519   1.0000   0.0495
  -9.250  -0.4112   0.08424   0.08110  -0.0552   1.0000   0.0497
  -9.000  -0.4309   0.08055   0.07744  -0.0551   1.0000   0.0496
  -8.750  -0.4562   0.07786   0.07478  -0.0536   1.0000   0.0495
  -8.500  -0.4739   0.07547   0.07245  -0.0511   1.0000   0.0492
  -8.250  -0.5085   0.07382   0.07081  -0.0486   0.9994   0.0493
  -8.000  -0.5006   0.06800   0.06434  -0.0632   0.9867   0.0503
  -7.750  -0.4924   0.05870   0.05513  -0.0668   0.9812   0.0522
  -7.500  -0.4628   0.05593   0.05247  -0.0694   0.9771   0.0559
  -7.250  -0.3783   0.03425   0.03055  -0.0810   0.9526   0.0669
  -7.000  -0.3543   0.03047   0.02663  -0.0838   0.9466   0.0709
  -6.750  -0.3349   0.02603   0.02174  -0.0872   0.9384   0.0801
  -6.500  -0.3525   0.03281   0.02707  -0.0846   0.9499   0.0369
  -6.250  -0.3245   0.02798   0.02166  -0.0853   0.9418   0.0326
  -6.000  -0.2851   0.02494   0.01816  -0.0873   0.9379   0.0319
  -5.750  -0.2479   0.02353   0.01666  -0.0893   0.9324   0.0349
  -5.500  -0.2119   0.02196   0.01486  -0.0906   0.9258   0.0372
  -5.250  -0.1700   0.02051   0.01322  -0.0927   0.9226   0.0389
  -5.000  -0.1399   0.01859   0.01141  -0.0932   0.9149   0.0436
  -4.750  -0.0990   0.01745   0.01023  -0.0956   0.9097   0.0490
  -4.500  -0.0588   0.01601   0.00883  -0.0985   0.9030   0.0576
  -4.250  -0.0145   0.01471   0.00752  -0.1024   0.8952   0.0736
  -4.000   0.0364   0.01133   0.00632  -0.1104   0.8877   0.5385
  -3.750   0.0773   0.01165   0.00667  -0.1118   0.8772   0.6130
  -3.500   0.1123   0.01222   0.00713  -0.1119   0.8626   0.6427
  -3.250   0.1422   0.01297   0.00780  -0.1107   0.8464   0.6608
  -3.000   0.1661   0.01390   0.00866  -0.1079   0.8283   0.6775
  -2.750   0.1905   0.01462   0.00928  -0.1055   0.8105   0.6907
  -2.500   0.2210   0.01480   0.00927  -0.1057   0.7931   0.7015
  -2.250   0.2465   0.01501   0.00933  -0.1044   0.7764   0.7056
  -2.000   0.2766   0.01504   0.00916  -0.1049   0.7602   0.7137
  -1.750   0.3023   0.01511   0.00908  -0.1042   0.7447   0.7183
  -1.500   0.3271   0.01521   0.00905  -0.1033   0.7298   0.7230
  -1.250   0.3575   0.01517   0.00883  -0.1043   0.7156   0.7308
  -1.000   0.3801   0.01526   0.00883  -0.1028   0.7024   0.7341
  -0.750   0.4057   0.01532   0.00878  -0.1023   0.6899   0.7391
  -0.500   0.4360   0.01530   0.00861  -0.1033   0.6780   0.7457
  -0.250   0.4599   0.01539   0.00860  -0.1022   0.6675   0.7490
   0.000   0.4851   0.01543   0.00857  -0.1018   0.6564   0.7538
   0.250   0.5157   0.01544   0.00847  -0.1029   0.6456   0.7601
   0.500   0.5396   0.01550   0.00845  -0.1019   0.6366   0.7631
   0.750   0.5647   0.01554   0.00846  -0.1014   0.6269   0.7672
   1.000   0.5950   0.01560   0.00843  -0.1024   0.6178   0.7727
   1.250   0.6216   0.01564   0.00840  -0.1023   0.6097   0.7763
   1.500   0.6454   0.01569   0.00845  -0.1015   0.6009   0.7799
   1.750   0.6745   0.01580   0.00847  -0.1020   0.5936   0.7842
   2.000   0.7041   0.01585   0.00852  -0.1029   0.5849   0.7891
   2.250   0.7292   0.01593   0.00854  -0.1023   0.5781   0.7921
   2.500   0.7535   0.01598   0.00864  -0.1017   0.5698   0.7958
   2.750   0.7837   0.01612   0.00870  -0.1025   0.5632   0.8001
   3.000   0.8114   0.01618   0.00880  -0.1029   0.5548   0.8041
   3.500   0.8617   0.01636   0.00901  -0.1021   0.5406   0.8107
   3.750   0.8917   0.01651   0.00910  -0.1029   0.5341   0.8146
   4.000   0.9197   0.01663   0.00929  -0.1034   0.5264   0.8182
   4.250   0.9453   0.01673   0.00939  -0.1030   0.5201   0.8212
   4.500   0.9700   0.01687   0.00961  -0.1026   0.5132   0.8247
   4.750   0.9982   0.01702   0.00977  -0.1030   0.5064   0.8283
   5.000   1.0277   0.01724   0.01004  -0.1038   0.4996   0.8318
   5.250   1.0521   0.01735   0.01021  -0.1033   0.4929   0.8348
   5.500   1.0786   0.01755   0.01043  -0.1033   0.4870   0.8381
   5.750   1.1037   0.01771   0.01070  -0.1031   0.4795   0.8415
   6.000   1.1344   0.01797   0.01093  -0.1040   0.4734   0.8450
   6.250   1.1576   0.01813   0.01126  -0.1034   0.4659   0.8482
   6.500   1.1841   0.01830   0.01143  -0.1033   0.4595   0.8514
   6.750   1.2064   0.01845   0.01173  -0.1025   0.4508   0.8549
   7.000   1.2340   0.01864   0.01193  -0.1028   0.4430   0.8585
   7.250   1.2565   0.01876   0.01220  -0.1021   0.4337   0.8620
   7.500   1.2779   0.01887   0.01238  -0.1010   0.4247   0.8653
   7.750   1.3009   0.01898   0.01252  -0.1003   0.4154   0.8688
   8.000   1.3217   0.01913   0.01284  -0.0993   0.4050   0.8729
   8.250   1.3416   0.01923   0.01303  -0.0981   0.3934   0.8766
   8.500   1.3583   0.01930   0.01317  -0.0962   0.3811   0.8804
   8.750   1.3757   0.01944   0.01337  -0.0946   0.3683   0.8845
   9.000   1.3942   0.01969   0.01369  -0.0933   0.3559   0.8890
   9.250   1.4084   0.01990   0.01405  -0.0911   0.3434   0.8936
   9.500   1.4217   0.02017   0.01446  -0.0888   0.3299   0.8986
   9.750   1.4332   0.02055   0.01489  -0.0863   0.3140   0.9038
  10.000   1.4388   0.02098   0.01537  -0.0828   0.2963   0.9103
  10.250   1.4445   0.02161   0.01603  -0.0796   0.2736   0.9181
  10.500   1.4443   0.02237   0.01678  -0.0755   0.2501   0.9281
  10.750   1.4399   0.02338   0.01776  -0.0711   0.2240   0.9447
  11.000   1.4362   0.02485   0.01914  -0.0678   0.1920   1.0000
  11.250   1.4297   0.02723   0.02132  -0.0653   0.1558   1.0000
  11.500   1.4208   0.03004   0.02396  -0.0630   0.1257   1.0000
  11.750   1.4109   0.03319   0.02698  -0.0613   0.1015   1.0000
  12.000   1.4021   0.03651   0.03023  -0.0601   0.0830   1.0000
  12.250   1.3938   0.04003   0.03374  -0.0595   0.0697   1.0000
  12.500   1.3865   0.04366   0.03739  -0.0592   0.0603   1.0000
  12.750   1.3765   0.04778   0.04150  -0.0592   0.0537   1.0000
  13.000   1.3730   0.05138   0.04521  -0.0596   0.0472   1.0000
  13.250   1.3629   0.05586   0.04972  -0.0601   0.0424   1.0000
  13.500   1.3584   0.05982   0.05378  -0.0608   0.0369   1.0000
  13.750   1.3455   0.06499   0.05900  -0.0619   0.0329   1.0000
  14.000   1.3373   0.06972   0.06384  -0.0630   0.0281   1.0000
  14.250   1.3191   0.07590   0.07006  -0.0645   0.0255   1.0000
  14.500   1.3138   0.08052   0.07481  -0.0657   0.0224   1.0000
  14.750   1.3066   0.08544   0.07980  -0.0672   0.0205   1.0000
  15.000   1.2965   0.09071   0.08510  -0.0686   0.0192   1.0000
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