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FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il)
Reynolds number: 50,000
Max Cl/Cd: 12.66 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66s171-il-50000-n5.txt
Download as CSV file: xf-fx66s171-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-171 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3518   0.09493   0.08865  -0.0639   1.0000   0.0490
 -11.000  -0.3629   0.08928   0.08309  -0.0665   1.0000   0.0487
 -10.750  -0.3775   0.08383   0.07773  -0.0692   1.0000   0.0484
 -10.500  -0.3987   0.07855   0.07256  -0.0717   1.0000   0.0481
 -10.250  -0.4161   0.07306   0.06711  -0.0759   0.9811   0.0478
 -10.000  -0.4258   0.06570   0.05951  -0.0855   0.9426   0.0475
  -9.750  -0.4317   0.05970   0.05313  -0.0932   0.9127   0.0475
  -9.500  -0.4320   0.05498   0.04794  -0.0975   0.8895   0.0478
  -9.250  -0.4284   0.05100   0.04340  -0.0998   0.8704   0.0484
  -9.000  -0.4172   0.04788   0.03990  -0.1008   0.8543   0.0499
  -8.750  -0.4004   0.04571   0.03756  -0.1013   0.8398   0.0523
  -8.500  -0.3849   0.04358   0.03511  -0.1013   0.8266   0.0549
  -8.250  -0.3676   0.04133   0.03243  -0.1010   0.8152   0.0573
  -8.000  -0.3484   0.03936   0.02991  -0.1004   0.8044   0.0602
  -7.750  -0.3276   0.03786   0.02845  -0.0999   0.7937   0.0643
  -7.500  -0.3050   0.03649   0.02683  -0.0991   0.7848   0.0693
  -7.250  -0.2827   0.03522   0.02536  -0.0981   0.7758   0.0747
  -7.000  -0.2637   0.03419   0.02427  -0.0971   0.7673   0.0816
  -6.750  -0.2450   0.03312   0.02308  -0.0958   0.7595   0.0891
  -6.500  -0.2284   0.03219   0.02200  -0.0947   0.7520   0.0999
  -6.250  -0.2139   0.03111   0.02095  -0.0935   0.7449   0.1130
  -6.000  -0.2000   0.02991   0.01986  -0.0926   0.7387   0.1325
  -5.750  -0.1883   0.02857   0.01877  -0.0916   0.7316   0.1671
  -5.500  -0.1765   0.02698   0.01790  -0.0907   0.7264   0.2549
  -5.250  -0.1608   0.02711   0.01857  -0.0886   0.7195   0.3722
  -5.000  -0.1385   0.02781   0.01911  -0.0870   0.7137   0.4347
  -4.750  -0.1153   0.02849   0.01952  -0.0857   0.7089   0.4765
  -4.500  -0.0954   0.02926   0.02016  -0.0839   0.7029   0.5065
  -4.250  -0.0725   0.03002   0.02081  -0.0817   0.6982   0.5300
  -4.000  -0.0483   0.03029   0.02083  -0.0806   0.6943   0.5522
  -3.750  -0.0293   0.03064   0.02107  -0.0791   0.6881   0.5677
  -3.500  -0.0063   0.03080   0.02108  -0.0779   0.6835   0.5801
  -3.250   0.0193   0.03077   0.02083  -0.0773   0.6799   0.5913
  -3.000   0.0393   0.03086   0.02077  -0.0768   0.6747   0.6016
  -2.750   0.0612   0.03093   0.02070  -0.0762   0.6700   0.6103
  -2.500   0.0864   0.03085   0.02042  -0.0761   0.6663   0.6187
  -2.250   0.1120   0.03080   0.02016  -0.0761   0.6628   0.6269
  -2.000   0.1302   0.03107   0.02037  -0.0755   0.6572   0.6338
  -1.750   0.1540   0.03116   0.02031  -0.0753   0.6530   0.6415
  -1.500   0.1804   0.03114   0.02012  -0.0754   0.6498   0.6490
  -1.250   0.2007   0.03143   0.02032  -0.0749   0.6455   0.6563
  -1.000   0.2193   0.03182   0.02064  -0.0743   0.6405   0.6637
  -0.750   0.2430   0.03201   0.02072  -0.0741   0.6368   0.6714
  -0.500   0.2703   0.03208   0.02066  -0.0742   0.6340   0.6797
  -0.250   0.2852   0.03274   0.02131  -0.0732   0.6289   0.6877
   0.000   0.3027   0.03329   0.02182  -0.0725   0.6241   0.6959
   0.250   0.3270   0.03355   0.02200  -0.0724   0.6208   0.7047
   0.500   0.3539   0.03369   0.02208  -0.0724   0.6182   0.7132
   0.750   0.3611   0.03488   0.02329  -0.0710   0.6122   0.7221
   1.000   0.3778   0.03551   0.02393  -0.0700   0.6077   0.7305
   1.250   0.4034   0.03578   0.02415  -0.0701   0.6046   0.7406
   1.500   0.4322   0.03588   0.02420  -0.0702   0.6024   0.7512
   1.750   0.4241   0.03786   0.02632  -0.0674   0.5943   0.7610
   2.000   0.4454   0.03832   0.02678  -0.0669   0.5905   0.7735
   2.250   0.4739   0.03838   0.02685  -0.0669   0.5880   0.7877
   2.500   0.4650   0.04047   0.02907  -0.0642   0.5798   0.8025
   2.750   0.4828   0.04105   0.02973  -0.0633   0.5756   0.8207
   3.000   0.5113   0.04112   0.02985  -0.0633   0.5730   0.8441
   3.500   0.5338   0.04428   0.03327  -0.0636   0.5600   1.0000
   3.750   0.5663   0.04473   0.03362  -0.0651   0.5575   1.0000
   4.250   0.5721   0.04916   0.03793  -0.0642   0.5441   1.0000
   4.500   0.6032   0.04956   0.03826  -0.0649   0.5418   1.0000
   4.750   0.5840   0.05329   0.04198  -0.0635   0.5321   1.0000
   5.000   0.6076   0.05418   0.04283  -0.0637   0.5288   1.0000
   5.250   0.6379   0.05463   0.04325  -0.0642   0.5265   1.0000
   5.500   0.6196   0.05831   0.04693  -0.0628   0.5167   1.0000
   5.750   0.6430   0.05923   0.04784  -0.0629   0.5134   1.0000
   6.000   0.6724   0.05974   0.04836  -0.0632   0.5112   1.0000
   6.250   0.6537   0.06352   0.05215  -0.0620   0.5012   1.0000
   6.500   0.6769   0.06447   0.05312  -0.0621   0.4980   1.0000
   7.000   0.6865   0.06897   0.05767  -0.0613   0.4857   1.0000
   7.250   0.7094   0.06999   0.05874  -0.0613   0.4826   1.0000
   7.500   0.7074   0.07284   0.06163  -0.0609   0.4760   1.0000
   7.750   0.7180   0.07472   0.06356  -0.0607   0.4705   1.0000
   8.000   0.7414   0.07570   0.06460  -0.0607   0.4674   1.0000
   8.250   0.7356   0.07895   0.06790  -0.0604   0.4602   1.0000
   8.500   0.7490   0.08067   0.06971  -0.0603   0.4553   1.0000
   8.750   0.7738   0.08153   0.07064  -0.0603   0.4522   1.0000
   9.000   0.7645   0.08506   0.07424  -0.0601   0.4439   1.0000
   9.250   0.7827   0.08642   0.07569  -0.0600   0.4395   1.0000
   9.500   0.8102   0.08702   0.07641  -0.0599   0.4367   1.0000
   9.750   0.7961   0.09102   0.08048  -0.0599   0.4271   1.0000
  10.000   0.8189   0.09199   0.08157  -0.0598   0.4234   1.0000
  10.250   0.8144   0.09531   0.08497  -0.0599   0.4154   1.0000
  10.500   0.8312   0.09677   0.08655  -0.0598   0.4105   1.0000
  10.750   0.8394   0.09898   0.08887  -0.0598   0.4042   1.0000
  11.000   0.8470   0.10124   0.09127  -0.0599   0.3974   1.0000
  11.250   0.8741   0.10163   0.09181  -0.0596   0.3938   1.0000
  11.500   0.8653   0.10542   0.09569  -0.0600   0.3838   1.0000
  11.750   0.8919   0.10572   0.09616  -0.0596   0.3797   1.0000
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