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FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.82 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx6617a2-il-1000000.txt
Download as CSV file: xf-fx6617a2-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-17AII-182 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.7174   0.08076   0.07844  -0.0652   1.0000   0.0076
 -16.000  -0.7465   0.07184   0.06932  -0.0703   1.0000   0.0074
 -15.750  -0.7539   0.06698   0.06437  -0.0731   1.0000   0.0073
 -15.500  -0.7832   0.05924   0.05643  -0.0772   1.0000   0.0074
 -15.250  -0.7960   0.05444   0.05150  -0.0795   1.0000   0.0074
 -15.000  -0.8116   0.04976   0.04670  -0.0813   1.0000   0.0076
 -14.750  -0.8204   0.04623   0.04305  -0.0824   1.0000   0.0077
 -14.500  -0.8124   0.04256   0.03926  -0.0862   0.9921   0.0078
 -14.250  -0.7303   0.03668   0.03305  -0.1081   0.9220   0.0080
 -14.000  -0.6861   0.03392   0.02963  -0.1179   0.8050   0.0082
 -13.750  -0.6838   0.03258   0.02806  -0.1169   0.7633   0.0083
 -13.500  -0.6771   0.03147   0.02678  -0.1162   0.7343   0.0085
 -13.250  -0.6742   0.02995   0.02509  -0.1154   0.7127   0.0086
 -13.000  -0.6731   0.02830   0.02327  -0.1143   0.6955   0.0086
 -12.750  -0.6656   0.02714   0.02198  -0.1135   0.6811   0.0089
 -12.500  -0.6587   0.02593   0.02064  -0.1125   0.6691   0.0089
 -12.250  -0.6506   0.02484   0.01943  -0.1115   0.6585   0.0091
 -12.000  -0.6431   0.02369   0.01817  -0.1104   0.6492   0.0092
 -11.750  -0.6325   0.02281   0.01718  -0.1095   0.6413   0.0094
 -11.500  -0.6251   0.02172   0.01599  -0.1081   0.6343   0.0095
 -11.250  -0.6175   0.02075   0.01491  -0.1066   0.6276   0.0096
 -11.000  -0.6193   0.01939   0.01346  -0.1039   0.6225   0.0098
 -10.750  -0.6143   0.01865   0.01265  -0.1011   0.6173   0.0100
 -10.500  -0.6036   0.01821   0.01213  -0.0990   0.6119   0.0102
 -10.250  -0.5851   0.01784   0.01173  -0.0979   0.6078   0.0105
 -10.000  -0.5675   0.01739   0.01124  -0.0968   0.6036   0.0108
  -9.750  -0.5476   0.01707   0.01086  -0.0959   0.5995   0.0113
  -9.500  -0.5283   0.01668   0.01039  -0.0949   0.5957   0.0117
  -9.250  -0.5073   0.01629   0.00995  -0.0941   0.5928   0.0122
  -9.000  -0.4889   0.01572   0.00933  -0.0930   0.5896   0.0129
  -8.750  -0.4674   0.01537   0.00895  -0.0923   0.5864   0.0135
  -8.500  -0.4440   0.01515   0.00870  -0.0918   0.5832   0.0143
  -8.250  -0.4196   0.01500   0.00849  -0.0914   0.5800   0.0153
  -8.000  -0.3925   0.01496   0.00841  -0.0914   0.5777   0.0160
  -7.750  -0.3765   0.01407   0.00749  -0.0900   0.5753   0.0175
  -7.500  -0.3523   0.01381   0.00721  -0.0896   0.5725   0.0187
  -7.250  -0.3282   0.01354   0.00689  -0.0892   0.5699   0.0196
  -7.000  -0.3033   0.01335   0.00665  -0.0889   0.5672   0.0201
  -6.750  -0.2833   0.01276   0.00597  -0.0879   0.5646   0.0214
  -6.500  -0.2593   0.01240   0.00560  -0.0875   0.5629   0.0224
  -6.250  -0.2343   0.01212   0.00530  -0.0872   0.5610   0.0232
  -6.000  -0.2090   0.01186   0.00501  -0.0869   0.5590   0.0239
  -5.750  -0.1833   0.01164   0.00475  -0.0866   0.5569   0.0247
  -5.500  -0.1573   0.01146   0.00453  -0.0865   0.5547   0.0252
  -5.250  -0.1328   0.01116   0.00416  -0.0860   0.5524   0.0266
  -5.000  -0.1073   0.01098   0.00395  -0.0858   0.5496   0.0283
  -4.750  -0.0809   0.01080   0.00375  -0.0856   0.5480   0.0296
  -4.500  -0.0541   0.01063   0.00356  -0.0855   0.5465   0.0308
  -4.250  -0.0274   0.01045   0.00337  -0.0854   0.5447   0.0329
  -4.000  -0.0009   0.01027   0.00319  -0.0853   0.5428   0.0388
  -3.750   0.0231   0.00984   0.00295  -0.0848   0.5409   0.0842
  -3.500   0.0461   0.00935   0.00272  -0.0843   0.5389   0.1571
  -3.250   0.0685   0.00883   0.00249  -0.0837   0.5371   0.2500
  -3.000   0.0922   0.00846   0.00232  -0.0832   0.5348   0.3174
  -2.750   0.1139   0.00789   0.00214  -0.0825   0.5330   0.4335
  -2.500   0.1400   0.00769   0.00211  -0.0822   0.5316   0.4896
  -2.250   0.1677   0.00766   0.00211  -0.0823   0.5300   0.5185
  -2.000   0.1958   0.00766   0.00214  -0.0824   0.5282   0.5370
  -1.750   0.2242   0.00771   0.00218  -0.0825   0.5265   0.5519
  -1.500   0.2526   0.00775   0.00222  -0.0826   0.5249   0.5609
  -1.250   0.2810   0.00781   0.00223  -0.0828   0.5232   0.5678
  -1.000   0.3091   0.00787   0.00229  -0.0829   0.5214   0.5745
  -0.750   0.3374   0.00798   0.00234  -0.0831   0.5191   0.5790
  -0.500   0.3659   0.00804   0.00237  -0.0833   0.5174   0.5823
  -0.250   0.3942   0.00803   0.00238  -0.0834   0.5161   0.5860
   0.000   0.4225   0.00808   0.00244  -0.0836   0.5145   0.5912
   0.250   0.4510   0.00812   0.00246  -0.0838   0.5130   0.5941
   0.500   0.4795   0.00817   0.00248  -0.0840   0.5113   0.5965
   0.750   0.5077   0.00818   0.00249  -0.0842   0.5098   0.5993
   1.000   0.5358   0.00820   0.00252  -0.0844   0.5081   0.6017
   1.250   0.5638   0.00825   0.00256  -0.0845   0.5064   0.6039
   1.500   0.5918   0.00834   0.00262  -0.0847   0.5042   0.6061
   1.750   0.6200   0.00843   0.00269  -0.0849   0.5023   0.6084
   2.000   0.6481   0.00845   0.00273  -0.0851   0.5010   0.6109
   2.250   0.6762   0.00849   0.00278  -0.0853   0.4994   0.6130
   2.500   0.7041   0.00849   0.00280  -0.0855   0.4975   0.6154
   2.750   0.7319   0.00851   0.00284  -0.0856   0.4956   0.6174
   3.000   0.7596   0.00854   0.00289  -0.0857   0.4938   0.6195
   3.250   0.7873   0.00860   0.00295  -0.0859   0.4921   0.6216
   3.500   0.8149   0.00868   0.00303  -0.0860   0.4903   0.6238
   3.750   0.8426   0.00882   0.00315  -0.0862   0.4880   0.6257
   4.000   0.8703   0.00887   0.00323  -0.0863   0.4867   0.6277
   4.250   0.8978   0.00891   0.00330  -0.0865   0.4853   0.6295
   4.500   0.9251   0.00892   0.00337  -0.0865   0.4836   0.6321
   4.750   0.9522   0.00895   0.00345  -0.0866   0.4816   0.6344
   5.000   0.9788   0.00896   0.00348  -0.0865   0.4782   0.6365
   5.250   1.0048   0.00903   0.00354  -0.0863   0.4741   0.6388
   5.500   1.0315   0.00910   0.00363  -0.0863   0.4714   0.6411
   5.750   1.0584   0.00914   0.00373  -0.0864   0.4694   0.6433
   6.000   1.0850   0.00919   0.00382  -0.0863   0.4669   0.6455
   6.250   1.1107   0.00920   0.00388  -0.0861   0.4630   0.6486
   6.500   1.1357   0.00930   0.00398  -0.0858   0.4591   0.6514
   6.750   1.1616   0.00936   0.00411  -0.0857   0.4562   0.6547
   7.000   1.1877   0.00941   0.00421  -0.0855   0.4529   0.6574
   7.250   1.2129   0.00948   0.00431  -0.0853   0.4485   0.6605
   7.500   1.2359   0.00957   0.00443  -0.0846   0.4422   0.6642
   7.750   1.2607   0.00961   0.00453  -0.0842   0.4351   0.6678
   8.000   1.2826   0.00973   0.00465  -0.0834   0.4234   0.6713
   8.250   1.3014   0.00996   0.00483  -0.0819   0.4040   0.6747
   8.500   1.3164   0.01032   0.00511  -0.0798   0.3825   0.6784
   8.750   1.3296   0.01066   0.00541  -0.0774   0.3632   0.6825
   9.000   1.3317   0.01127   0.00590  -0.0729   0.3331   0.6868
   9.250   1.3278   0.01216   0.00661  -0.0675   0.2988   0.6911
   9.500   1.3104   0.01350   0.00773  -0.0602   0.2537   0.6959
   9.750   1.2985   0.01477   0.00889  -0.0544   0.2230   0.7017
  10.000   1.2803   0.01652   0.01050  -0.0485   0.1908   0.7077
  10.250   1.2633   0.01860   0.01250  -0.0437   0.1634   0.7155
  10.500   1.2434   0.02136   0.01517  -0.0396   0.1348   0.7247
  10.750   1.2313   0.02402   0.01780  -0.0370   0.1146   0.7373
  11.000   1.2193   0.02691   0.02070  -0.0349   0.0940   0.7559
  11.250   1.2048   0.03024   0.02409  -0.0332   0.0719   0.8000
  11.500   1.2628   0.03701   0.03102  -0.0521   0.0275   0.9343
  11.750   1.2703   0.03971   0.03371  -0.0529   0.0208   1.0000
  12.000   1.2687   0.04236   0.03637  -0.0522   0.0167   1.0000
  12.250   1.2703   0.04478   0.03881  -0.0516   0.0153   1.0000
  12.500   1.2733   0.04714   0.04120  -0.0512   0.0142   1.0000
  12.750   1.2763   0.04950   0.04362  -0.0508   0.0135   1.0000
  13.000   1.2807   0.05175   0.04592  -0.0504   0.0132   1.0000
  13.250   1.2835   0.05419   0.04842  -0.0501   0.0128   1.0000
  13.500   1.2858   0.05670   0.05098  -0.0498   0.0123   1.0000
  13.750   1.2876   0.05930   0.05362  -0.0495   0.0119   1.0000
  14.000   1.2864   0.06223   0.05661  -0.0491   0.0113   1.0000
  14.250   1.2866   0.06508   0.05953  -0.0489   0.0108   1.0000
  14.500   1.2925   0.06731   0.06181  -0.0488   0.0106   1.0000
  14.750   1.2967   0.06971   0.06427  -0.0487   0.0101   1.0000
  15.000   1.2990   0.07238   0.06699  -0.0486   0.0098   1.0000
  15.250   1.2998   0.07523   0.06990  -0.0485   0.0096   1.0000
  15.500   1.3009   0.07811   0.07283  -0.0485   0.0092   1.0000
  15.750   1.3022   0.08094   0.07571  -0.0486   0.0090   1.0000
  16.000   1.2928   0.08509   0.07994  -0.0486   0.0084   1.0000
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