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FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il)
Reynolds number: 200,000
Max Cl/Cd: 67.37 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx6617a2-il-200000-n5.txt
Download as CSV file: xf-fx6617a2-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.3138   0.09250   0.08831  -0.0859   0.7978   0.0158
 -13.250  -0.3520   0.07867   0.07435  -0.0944   0.7914   0.0155
 -13.000  -0.3781   0.06950   0.06497  -0.1011   0.7758   0.0152
 -12.750  -0.4088   0.06154   0.05671  -0.1066   0.7616   0.0152
 -12.500  -0.4289   0.05635   0.05126  -0.1094   0.7460   0.0151
 -12.250  -0.4487   0.05185   0.04649  -0.1110   0.7329   0.0152
 -12.000  -0.4652   0.04804   0.04239  -0.1118   0.7210   0.0152
 -11.750  -0.4802   0.04456   0.03861  -0.1119   0.7103   0.0153
 -11.500  -0.4900   0.04168   0.03545  -0.1115   0.7009   0.0154
 -11.250  -0.4990   0.03899   0.03243  -0.1106   0.6925   0.0156
 -11.000  -0.5057   0.03661   0.02971  -0.1093   0.6846   0.0159
 -10.750  -0.5067   0.03461   0.02744  -0.1077   0.6773   0.0161
 -10.500  -0.5006   0.03306   0.02575  -0.1064   0.6705   0.0163
 -10.250  -0.4936   0.03182   0.02438  -0.1047   0.6639   0.0167
 -10.000  -0.4857   0.03077   0.02318  -0.1029   0.6583   0.0171
  -9.750  -0.4743   0.02959   0.02184  -0.1015   0.6525   0.0176
  -9.500  -0.4603   0.02844   0.02051  -0.1003   0.6473   0.0183
  -9.250  -0.4446   0.02732   0.01916  -0.0991   0.6430   0.0191
  -9.000  -0.4281   0.02643   0.01802  -0.0980   0.6384   0.0202
  -8.750  -0.4109   0.02532   0.01692  -0.0971   0.6341   0.0212
  -8.500  -0.3931   0.02459   0.01611  -0.0962   0.6303   0.0223
  -8.250  -0.3745   0.02384   0.01524  -0.0952   0.6269   0.0236
  -8.000  -0.3552   0.02307   0.01434  -0.0943   0.6228   0.0247
  -7.750  -0.3371   0.02225   0.01345  -0.0932   0.6189   0.0258
  -7.500  -0.3185   0.02164   0.01281  -0.0923   0.6155   0.0273
  -7.250  -0.2987   0.02111   0.01219  -0.0915   0.6124   0.0290
  -7.000  -0.2777   0.02062   0.01160  -0.0907   0.6093   0.0308
  -6.750  -0.2590   0.01993   0.01089  -0.0898   0.6062   0.0323
  -6.500  -0.2390   0.01936   0.01027  -0.0889   0.6032   0.0336
  -6.250  -0.2178   0.01890   0.00973  -0.0882   0.6005   0.0355
  -6.000  -0.1959   0.01848   0.00920  -0.0876   0.5980   0.0375
  -5.750  -0.1737   0.01806   0.00867  -0.0869   0.5956   0.0391
  -5.500  -0.1520   0.01756   0.00814  -0.0863   0.5926   0.0417
  -5.250  -0.1289   0.01718   0.00771  -0.0858   0.5896   0.0454
  -5.000  -0.1059   0.01678   0.00728  -0.0852   0.5869   0.0525
  -4.750  -0.0832   0.01633   0.00687  -0.0847   0.5845   0.0721
  -4.500  -0.0621   0.01572   0.00646  -0.0841   0.5824   0.1237
  -4.000  -0.0221   0.01431   0.00570  -0.0827   0.5782   0.2995
  -3.750  -0.0033   0.01368   0.00560  -0.0815   0.5758   0.4221
  -3.500   0.0206   0.01369   0.00586  -0.0807   0.5733   0.5011
  -3.250   0.0472   0.01386   0.00598  -0.0804   0.5708   0.5353
  -3.000   0.0743   0.01403   0.00608  -0.0801   0.5685   0.5545
  -2.750   0.1013   0.01429   0.00627  -0.0798   0.5665   0.5742
  -2.250   0.1555   0.01466   0.00645  -0.0794   0.5626   0.5975
  -2.000   0.1828   0.01472   0.00651  -0.0793   0.5602   0.6015
  -1.750   0.2100   0.01479   0.00652  -0.0793   0.5577   0.6064
  -1.500   0.2374   0.01484   0.00646  -0.0793   0.5554   0.6118
  -1.250   0.2649   0.01490   0.00646  -0.0793   0.5534   0.6160
  -1.000   0.2925   0.01497   0.00649  -0.0794   0.5516   0.6201
  -0.750   0.3204   0.01504   0.00646  -0.0795   0.5500   0.6240
  -0.500   0.3479   0.01511   0.00644  -0.0796   0.5481   0.6278
  -0.250   0.3746   0.01515   0.00648  -0.0796   0.5456   0.6305
   0.000   0.4016   0.01519   0.00653  -0.0796   0.5433   0.6329
   0.250   0.4287   0.01525   0.00657  -0.0796   0.5411   0.6355
   0.500   0.4561   0.01532   0.00660  -0.0797   0.5392   0.6382
   0.750   0.4836   0.01539   0.00663  -0.0799   0.5374   0.6413
   1.000   0.5113   0.01547   0.00664  -0.0801   0.5357   0.6447
   1.250   0.5392   0.01554   0.00668  -0.0803   0.5341   0.6471
   1.500   0.5657   0.01564   0.00680  -0.0802   0.5321   0.6496
   1.750   0.5916   0.01574   0.00696  -0.0801   0.5297   0.6526
   2.000   0.6179   0.01585   0.00709  -0.0800   0.5275   0.6559
   2.250   0.6446   0.01596   0.00720  -0.0801   0.5255   0.6589
   2.500   0.6715   0.01607   0.00730  -0.0801   0.5236   0.6614
   2.750   0.6985   0.01615   0.00742  -0.0802   0.5219   0.6635
   3.000   0.7259   0.01624   0.00751  -0.0803   0.5201   0.6660
   3.250   0.7536   0.01635   0.00760  -0.0805   0.5185   0.6689
   3.500   0.7788   0.01651   0.00784  -0.0803   0.5163   0.6717
   3.750   0.8035   0.01668   0.00808  -0.0801   0.5140   0.6745
   4.000   0.8288   0.01684   0.00829  -0.0799   0.5117   0.6772
   4.250   0.8543   0.01696   0.00850  -0.0797   0.5094   0.6797
   4.500   0.8804   0.01708   0.00867  -0.0797   0.5074   0.6827
   4.750   0.9071   0.01720   0.00882  -0.0797   0.5056   0.6859
   5.000   0.9343   0.01733   0.00897  -0.0799   0.5040   0.6892
   5.250   0.9603   0.01751   0.00919  -0.0798   0.5020   0.6924
   5.500   0.9820   0.01774   0.00959  -0.0791   0.4993   0.6952
   5.750   1.0052   0.01797   0.00993  -0.0786   0.4969   0.6983
   6.000   1.0294   0.01818   0.01025  -0.0783   0.4947   0.7021
   6.250   1.0545   0.01837   0.01051  -0.0781   0.4927   0.7064
   6.500   1.0803   0.01852   0.01074  -0.0780   0.4908   0.7102
   6.750   1.1069   0.01865   0.01095  -0.0781   0.4890   0.7142
   7.000   1.1326   0.01883   0.01122  -0.0780   0.4872   0.7187
   7.250   1.1508   0.01922   0.01178  -0.0768   0.4842   0.7235
   7.500   1.1708   0.01953   0.01227  -0.0758   0.4816   0.7280
   7.750   1.1924   0.01971   0.01258  -0.0750   0.4786   0.7336
   8.000   1.2173   0.01974   0.01269  -0.0747   0.4756   0.7400
   8.250   1.2423   0.01969   0.01273  -0.0744   0.4716   0.7469
   8.750   1.2787   0.01979   0.01312  -0.0716   0.4600   0.7647
   9.000   1.2954   0.01993   0.01342  -0.0700   0.4544   0.7763
   9.250   1.3092   0.02003   0.01369  -0.0678   0.4473   0.7923
   9.750   1.3495   0.02003   0.01418  -0.0666   0.4240   0.9315
  10.000   1.3478   0.02047   0.01461  -0.0622   0.4091   1.0000
  10.250   1.3487   0.02119   0.01532  -0.0588   0.3911   1.0000
  10.500   1.3465   0.02228   0.01632  -0.0556   0.3707   1.0000
  10.750   1.3459   0.02366   0.01770  -0.0531   0.3539   1.0000
  11.000   1.3400   0.02557   0.01957  -0.0506   0.3325   1.0000
  11.250   1.3285   0.02816   0.02207  -0.0483   0.3096   1.0000
  11.500   1.3111   0.03151   0.02531  -0.0461   0.2811   1.0000
  11.750   1.2921   0.03524   0.02893  -0.0443   0.2571   1.0000
  12.000   1.2708   0.03936   0.03293  -0.0427   0.2329   1.0000
  12.250   1.2489   0.04366   0.03712  -0.0413   0.2084   1.0000
  12.500   1.2319   0.04771   0.04108  -0.0403   0.1861   1.0000
  12.750   1.2109   0.05234   0.04555  -0.0394   0.1589   1.0000
  13.000   1.1994   0.05615   0.04928  -0.0388   0.1392   1.0000
  13.250   1.1857   0.06031   0.05330  -0.0384   0.1151   1.0000
  13.500   1.1770   0.06404   0.05693  -0.0381   0.0958   1.0000
  13.750   1.1683   0.06782   0.06061  -0.0379   0.0769   1.0000
  14.000   1.1629   0.07133   0.06404  -0.0378   0.0615   1.0000
  14.250   1.1594   0.07469   0.06735  -0.0378   0.0493   1.0000
  14.500   1.1581   0.07783   0.07048  -0.0379   0.0409   1.0000
  14.750   1.1564   0.08107   0.07371  -0.0380   0.0340   1.0000
  15.000   1.1562   0.08419   0.07683  -0.0382   0.0290   1.0000
  15.250   1.1572   0.08721   0.07990  -0.0384   0.0247   1.0000
  15.750   1.1604   0.09317   0.08599  -0.0390   0.0207   1.0000
  16.000   1.1626   0.09612   0.08900  -0.0394   0.0192   1.0000
  16.250   1.1630   0.09932   0.09224  -0.0399   0.0179   1.0000
  16.500   1.1640   0.10249   0.09548  -0.0404   0.0171   1.0000
  16.750   1.1656   0.10561   0.09869  -0.0410   0.0163   1.0000
  17.000   1.1666   0.10880   0.10196  -0.0417   0.0155   1.0000
  17.250   1.1673   0.11207   0.10530  -0.0424   0.0150   1.0000
  17.500   1.1666   0.11558   0.10887  -0.0433   0.0145   1.0000
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