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(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: (Dicke 12.28%) (e171-il)
Reynolds number: 500,000
Max Cl/Cd: 56.8 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e171-il-500000-n5.txt
Download as CSV file: xf-e171-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: (Dicke 12.28%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.8346   0.13333   0.13090   0.0115   1.0000   0.0040
 -16.250  -0.8794   0.11706   0.11446   0.0030   1.0000   0.0039
 -16.000  -0.9125   0.10458   0.10182  -0.0038   1.0000   0.0038
 -15.750  -0.9412   0.09370   0.09078  -0.0100   1.0000   0.0037
 -15.500  -0.9630   0.08483   0.08175  -0.0152   1.0000   0.0037
 -15.250  -0.9807   0.07727   0.07403  -0.0195   1.0000   0.0037
 -15.000  -0.9964   0.07063   0.06724  -0.0232   1.0000   0.0037
 -14.750  -1.0122   0.06447   0.06091  -0.0264   1.0000   0.0037
 -14.500  -1.0281   0.05878   0.05504  -0.0290   1.0000   0.0037
 -14.250  -1.0360   0.05448   0.05059  -0.0308   1.0000   0.0037
 -14.000  -1.0444   0.05037   0.04633  -0.0321   1.0000   0.0037
 -13.750  -1.0471   0.04714   0.04295  -0.0331   1.0000   0.0038
 -13.500  -1.0564   0.04328   0.03890  -0.0337   1.0000   0.0038
 -13.250  -1.0592   0.04033   0.03579  -0.0339   1.0000   0.0039
 -13.000  -1.0590   0.03783   0.03316  -0.0339   1.0000   0.0040
 -12.750  -1.0606   0.03527   0.03044  -0.0335   1.0000   0.0040
 -12.500  -1.0589   0.03315   0.02819  -0.0328   1.0000   0.0041
 -12.250  -1.0508   0.03175   0.02668  -0.0322   1.0000   0.0043
 -12.000  -1.0497   0.02975   0.02454  -0.0309   1.0000   0.0044
 -11.750  -1.0465   0.02808   0.02274  -0.0294   1.0000   0.0044
 -11.500  -1.0384   0.02691   0.02144  -0.0279   1.0000   0.0046
 -11.250  -1.0309   0.02577   0.02020  -0.0262   1.0000   0.0047
 -11.000  -1.0305   0.02421   0.01852  -0.0233   1.0000   0.0049
 -10.750  -1.0268   0.02302   0.01722  -0.0203   1.0000   0.0052
 -10.500  -1.0190   0.02207   0.01619  -0.0177   1.0000   0.0054
 -10.250  -1.0068   0.02119   0.01522  -0.0158   1.0000   0.0056
 -10.000  -0.9926   0.02037   0.01431  -0.0140   1.0000   0.0058
  -9.750  -0.9765   0.01968   0.01356  -0.0125   1.0000   0.0063
  -9.500  -0.9606   0.01893   0.01272  -0.0109   1.0000   0.0065
  -9.250  -0.9436   0.01825   0.01197  -0.0094   1.0000   0.0071
  -9.000  -0.9259   0.01762   0.01126  -0.0080   1.0000   0.0075
  -8.750  -0.9075   0.01703   0.01060  -0.0066   1.0000   0.0079
  -8.500  -0.8911   0.01627   0.00979  -0.0049   1.0000   0.0088
  -8.250  -0.8721   0.01576   0.00925  -0.0036   1.0000   0.0099
  -8.000  -0.8521   0.01533   0.00876  -0.0024   1.0000   0.0115
  -7.750  -0.8326   0.01487   0.00825  -0.0010   1.0000   0.0128
  -7.500  -0.8141   0.01433   0.00770   0.0004   1.0000   0.0146
  -7.000  -0.7516   0.01338   0.00666  -0.0019   0.9841   0.0188
  -6.750  -0.7194   0.01288   0.00616  -0.0032   0.9664   0.0230
  -6.500  -0.6814   0.01235   0.00562  -0.0058   0.9418   0.0320
  -6.250  -0.6451   0.01186   0.00513  -0.0080   0.9121   0.0460
  -6.000  -0.6191   0.01149   0.00473  -0.0078   0.8802   0.0613
  -5.750  -0.5963   0.01115   0.00438  -0.0069   0.8539   0.0820
  -5.500  -0.5735   0.01081   0.00405  -0.0061   0.8320   0.1052
  -5.000  -0.5266   0.01017   0.00345  -0.0048   0.7978   0.1585
  -4.750  -0.5034   0.00977   0.00315  -0.0041   0.7831   0.1983
  -4.500  -0.4805   0.00933   0.00286  -0.0034   0.7699   0.2499
  -4.250  -0.4579   0.00883   0.00257  -0.0027   0.7576   0.3112
  -4.000  -0.4348   0.00839   0.00234  -0.0021   0.7461   0.3729
  -3.750  -0.4098   0.00814   0.00216  -0.0016   0.7357   0.4137
  -3.500  -0.3846   0.00793   0.00204  -0.0012   0.7261   0.4544
  -3.250  -0.3584   0.00781   0.00195  -0.0009   0.7165   0.4817
  -3.000  -0.3314   0.00774   0.00187  -0.0007   0.7077   0.5005
  -2.500  -0.2771   0.00764   0.00172  -0.0004   0.6912   0.5309
  -2.250  -0.2496   0.00761   0.00166  -0.0003   0.6837   0.5433
  -2.000  -0.2221   0.00757   0.00162  -0.0002   0.6762   0.5544
  -1.750  -0.1946   0.00755   0.00157  -0.0002   0.6693   0.5649
  -1.500  -0.1669   0.00753   0.00153  -0.0001   0.6621   0.5745
  -1.250  -0.1392   0.00752   0.00150  -0.0001   0.6557   0.5836
  -1.000  -0.1114   0.00750   0.00147  -0.0001   0.6488   0.5916
  -0.500  -0.0557   0.00748   0.00144   0.0000   0.6361   0.6082
  -0.250  -0.0279   0.00748   0.00143   0.0000   0.6297   0.6160
   0.000   0.0000   0.00747   0.00143   0.0000   0.6232   0.6231
   0.250   0.0279   0.00748   0.00143   0.0000   0.6160   0.6297
   0.500   0.0557   0.00748   0.00144   0.0000   0.6082   0.6361
   1.000   0.1113   0.00750   0.00147   0.0001   0.5916   0.6488
   1.250   0.1392   0.00752   0.00150   0.0001   0.5836   0.6557
   1.500   0.1669   0.00753   0.00153   0.0001   0.5745   0.6621
   1.750   0.1946   0.00755   0.00157   0.0002   0.5649   0.6693
   2.000   0.2221   0.00757   0.00162   0.0002   0.5544   0.6762
   2.500   0.2771   0.00764   0.00172   0.0004   0.5309   0.6912
   3.000   0.3314   0.00774   0.00187   0.0007   0.5004   0.7077
   3.250   0.3584   0.00781   0.00195   0.0009   0.4817   0.7165
   3.500   0.3847   0.00793   0.00204   0.0012   0.4546   0.7261
   3.750   0.4098   0.00814   0.00216   0.0016   0.4136   0.7357
   4.000   0.4348   0.00839   0.00234   0.0020   0.3732   0.7462
   4.250   0.4582   0.00881   0.00257   0.0027   0.3138   0.7577
   4.500   0.4808   0.00930   0.00285   0.0034   0.2527   0.7699
   4.750   0.5036   0.00977   0.00315   0.0041   0.1985   0.7831
   5.000   0.5268   0.01017   0.00345   0.0047   0.1585   0.7978
   5.250   0.5504   0.01050   0.00373   0.0054   0.1297   0.8139
   5.500   0.5737   0.01081   0.00405   0.0061   0.1052   0.8319
   5.750   0.5965   0.01115   0.00438   0.0069   0.0820   0.8538
   6.000   0.6194   0.01149   0.00473   0.0077   0.0616   0.8800
   6.250   0.6452   0.01186   0.00513   0.0080   0.0458   0.9119
   6.500   0.6815   0.01235   0.00562   0.0058   0.0317   0.9419
   6.750   0.7195   0.01288   0.00616   0.0032   0.0231   0.9665
   7.000   0.7519   0.01338   0.00666   0.0018   0.0188   0.9843
   7.500   0.8139   0.01433   0.00770  -0.0004   0.0146   1.0000
   7.750   0.8322   0.01490   0.00828   0.0011   0.0126   1.0000
   8.000   0.8522   0.01532   0.00875   0.0024   0.0115   1.0000
   8.250   0.8721   0.01575   0.00925   0.0036   0.0100   1.0000
   8.500   0.8912   0.01627   0.00979   0.0049   0.0088   1.0000
   8.750   0.9078   0.01702   0.01058   0.0065   0.0079   1.0000
   9.000   0.9264   0.01760   0.01124   0.0079   0.0074   1.0000
   9.250   0.9440   0.01825   0.01197   0.0094   0.0070   1.0000
   9.500   0.9610   0.01894   0.01273   0.0108   0.0066   1.0000
   9.750   0.9772   0.01966   0.01353   0.0124   0.0062   1.0000
  10.000   0.9923   0.02045   0.01440   0.0140   0.0060   1.0000
  10.250   1.0076   0.02118   0.01522   0.0156   0.0056   1.0000
  10.500   1.0198   0.02208   0.01620   0.0175   0.0053   1.0000
  10.750   1.0279   0.02302   0.01723   0.0201   0.0052   1.0000
  11.000   1.0315   0.02423   0.01853   0.0231   0.0049   1.0000
  11.250   1.0300   0.02592   0.02037   0.0262   0.0047   1.0000
  11.500   1.0364   0.02717   0.02173   0.0280   0.0046   1.0000
  11.750   1.0432   0.02846   0.02312   0.0295   0.0045   1.0000
  12.000   1.0497   0.02987   0.02467   0.0308   0.0044   1.0000
  12.250   1.0560   0.03137   0.02628   0.0318   0.0042   1.0000
  12.500   1.0557   0.03359   0.02866   0.0328   0.0042   1.0000
  12.750   1.0599   0.03547   0.03066   0.0333   0.0041   1.0000
  13.000   1.0591   0.03798   0.03332   0.0337   0.0040   1.0000
  13.250   1.0563   0.04082   0.03632   0.0338   0.0039   1.0000
  13.500   1.0574   0.04333   0.03895   0.0335   0.0038   1.0000
  13.750   1.0524   0.04668   0.04248   0.0329   0.0038   1.0000
  14.000   1.0441   0.05061   0.04658   0.0319   0.0038   1.0000
  14.250   1.0358   0.05475   0.05088   0.0304   0.0037   1.0000
  14.500   1.0253   0.05941   0.05570   0.0285   0.0037   1.0000
  14.750   1.0116   0.06481   0.06126   0.0260   0.0037   1.0000
  15.000   0.9965   0.07091   0.06753   0.0228   0.0037   1.0000
  15.250   0.9801   0.07773   0.07451   0.0190   0.0037   1.0000
  15.500   0.9615   0.08549   0.08243   0.0145   0.0037   1.0000
  15.750   0.9355   0.09527   0.09239   0.0088   0.0038   1.0000
  16.000   0.9178   0.10387   0.10109   0.0039   0.0037   1.0000
  16.250   0.8819   0.11698   0.11438  -0.0033   0.0038   1.0000
  16.500   0.8362   0.13340   0.13096  -0.0118   0.0041   1.0000
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