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FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il)
Reynolds number: 100,000
Max Cl/Cd: 39.21 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66s171-il-100000-n5.txt
Download as CSV file: xf-fx66s171-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4735   0.06537   0.06047  -0.0783   0.9990   0.0247
 -11.000  -0.4796   0.05741   0.05213  -0.0894   0.9196   0.0247
 -10.750  -0.4770   0.05132   0.04557  -0.0984   0.8755   0.0248
 -10.500  -0.4746   0.04762   0.04154  -0.1018   0.8412   0.0252
 -10.250  -0.4780   0.04495   0.03852  -0.1021   0.8153   0.0254
 -10.000  -0.4772   0.04268   0.03595  -0.1015   0.7960   0.0257
  -9.750  -0.4721   0.04056   0.03353  -0.1008   0.7802   0.0261
  -9.500  -0.4639   0.03853   0.03120  -0.1001   0.7669   0.0266
  -9.250  -0.4526   0.03659   0.02894  -0.0994   0.7554   0.0273
  -9.000  -0.4387   0.03476   0.02680  -0.0986   0.7445   0.0281
  -8.750  -0.4226   0.03308   0.02481  -0.0978   0.7347   0.0295
  -8.500  -0.4043   0.03159   0.02294  -0.0971   0.7263   0.0313
  -8.250  -0.3853   0.03027   0.02161  -0.0967   0.7176   0.0330
  -8.000  -0.3649   0.02914   0.02033  -0.0962   0.7106   0.0351
  -7.750  -0.3440   0.02798   0.01900  -0.0955   0.7030   0.0371
  -7.500  -0.3232   0.02695   0.01779  -0.0948   0.6966   0.0400
  -7.250  -0.3037   0.02603   0.01687  -0.0942   0.6900   0.0433
  -7.000  -0.2832   0.02519   0.01591  -0.0934   0.6836   0.0467
  -6.750  -0.2634   0.02434   0.01497  -0.0926   0.6782   0.0515
  -6.500  -0.2431   0.02362   0.01420  -0.0919   0.6718   0.0569
  -6.250  -0.2230   0.02283   0.01331  -0.0911   0.6666   0.0637
  -6.000  -0.2015   0.02215   0.01253  -0.0906   0.6620   0.0740
  -5.750  -0.1808   0.02136   0.01177  -0.0901   0.6568   0.0886
  -5.500  -0.1596   0.02052   0.01100  -0.0897   0.6523   0.1169
  -5.250  -0.1393   0.01945   0.01018  -0.0895   0.6487   0.1812
  -5.000  -0.1206   0.01844   0.00983  -0.0891   0.6441   0.3124
  -4.750  -0.0967   0.01837   0.00998  -0.0885   0.6395   0.3877
  -4.500  -0.0703   0.01853   0.01001  -0.0881   0.6355   0.4297
  -4.250  -0.0436   0.01876   0.01007  -0.0877   0.6319   0.4589
  -4.000  -0.0178   0.01903   0.01027  -0.0872   0.6273   0.4810
  -3.750   0.0085   0.01927   0.01040  -0.0867   0.6235   0.5002
  -3.500   0.0350   0.01948   0.01048  -0.0863   0.6203   0.5168
  -3.250   0.0621   0.01963   0.01049  -0.0860   0.6175   0.5300
  -3.000   0.0880   0.01971   0.01049  -0.0857   0.6134   0.5406
  -2.750   0.1146   0.01974   0.01041  -0.0856   0.6095   0.5488
  -2.500   0.1419   0.01973   0.01026  -0.0856   0.6062   0.5555
  -2.250   0.1696   0.01972   0.01012  -0.0856   0.6034   0.5613
  -2.000   0.1969   0.01973   0.00996  -0.0858   0.6003   0.5681
  -1.750   0.2230   0.01977   0.01000  -0.0856   0.5965   0.5724
  -1.500   0.2499   0.01980   0.00996  -0.0856   0.5931   0.5781
  -1.250   0.2775   0.01983   0.00986  -0.0858   0.5903   0.5845
  -1.000   0.3051   0.01987   0.00982  -0.0858   0.5880   0.5896
  -0.750   0.3319   0.01996   0.00985  -0.0858   0.5850   0.5954
  -0.500   0.3577   0.02007   0.00995  -0.0858   0.5814   0.6009
  -0.250   0.3840   0.02017   0.01004  -0.0856   0.5782   0.6061
   0.000   0.4113   0.02026   0.01006  -0.0858   0.5755   0.6127
   0.250   0.4388   0.02034   0.01010  -0.0858   0.5733   0.6186
   0.500   0.4665   0.02045   0.01015  -0.0859   0.5713   0.6257
   0.750   0.4906   0.02070   0.01047  -0.0857   0.5677   0.6324
   1.000   0.5158   0.02088   0.01070  -0.0855   0.5643   0.6387
   1.250   0.5424   0.02104   0.01083  -0.0855   0.5614   0.6459
   1.500   0.5691   0.02115   0.01095  -0.0854   0.5590   0.6520
   1.750   0.5970   0.02127   0.01103  -0.0856   0.5570   0.6595
   2.000   0.6206   0.02154   0.01139  -0.0852   0.5537   0.6662
   2.250   0.6439   0.02182   0.01175  -0.0848   0.5497   0.6744
   2.500   0.6694   0.02198   0.01196  -0.0845   0.5464   0.6825
   2.750   0.6968   0.02209   0.01207  -0.0846   0.5437   0.6925
   3.000   0.7250   0.02215   0.01213  -0.0847   0.5415   0.7019
   3.250   0.7454   0.02259   0.01274  -0.0839   0.5374   0.7123
   3.500   0.7680   0.02293   0.01320  -0.0834   0.5339   0.7240
   3.750   0.7926   0.02317   0.01352  -0.0831   0.5311   0.7367
   4.000   0.8187   0.02331   0.01375  -0.0829   0.5288   0.7516
   4.250   0.8459   0.02337   0.01388  -0.0828   0.5267   0.7702
   4.500   0.8624   0.02389   0.01463  -0.0814   0.5226   0.7940
   4.750   0.8805   0.02424   0.01521  -0.0800   0.5187   0.8287
   5.000   0.9082   0.02437   0.01556  -0.0802   0.5158   0.8979
   5.250   0.9422   0.02457   0.01579  -0.0818   0.5134   1.0000
   5.500   0.9720   0.02479   0.01597  -0.0824   0.5115   1.0000
   5.750   0.9834   0.02585   0.01720  -0.0808   0.5065   1.0000
   6.000   1.0025   0.02650   0.01792  -0.0801   0.5024   1.0000
   6.250   1.0278   0.02684   0.01829  -0.0800   0.4995   1.0000
   6.500   1.0565   0.02703   0.01851  -0.0803   0.4973   1.0000
   6.750   1.0723   0.02785   0.01943  -0.0792   0.4934   1.0000
   7.000   1.0791   0.02905   0.02078  -0.0770   0.4879   1.0000
   7.250   1.1020   0.02945   0.02125  -0.0766   0.4847   1.0000
   7.500   1.1313   0.02957   0.02142  -0.0769   0.4823   1.0000
   7.750   1.1341   0.03094   0.02294  -0.0743   0.4771   1.0000
   8.000   1.1342   0.03241   0.02454  -0.0715   0.4716   1.0000
   8.250   1.1584   0.03271   0.02492  -0.0712   0.4689   1.0000
   8.500   1.1916   0.03261   0.02489  -0.0718   0.4669   1.0000
   9.000   1.0883   0.04188   0.03436  -0.0592   0.4461   1.0000
   9.250   1.1910   0.03678   0.02941  -0.0634   0.4522   1.0000
   9.750   1.0395   0.05414   0.04680  -0.0559   0.4172   1.0000
  10.000   1.0915   0.05105   0.04386  -0.0555   0.4205   1.0000
  10.250   1.1396   0.04859   0.04154  -0.0553   0.4220   1.0000
  11.750   1.0954   0.06908   0.06255  -0.0524   0.3676   1.0000
  12.750   1.1756   0.06756   0.06150  -0.0492   0.3341   1.0000
  13.000   1.1761   0.06972   0.06374  -0.0489   0.3172   1.0000
  13.250   1.1778   0.07195   0.06602  -0.0487   0.2991   1.0000
  13.500   1.1867   0.07328   0.06735  -0.0484   0.2785   1.0000
  13.750   1.1853   0.07630   0.07040  -0.0485   0.2572   1.0000
  14.000   1.1967   0.07718   0.07107  -0.0479   0.2215   1.0000
  14.250   1.1938   0.08012   0.07368  -0.0477   0.1833   1.0000
  14.500   1.1813   0.08472   0.07802  -0.0482   0.1521   1.0000
  14.750   1.1674   0.08981   0.08292  -0.0491   0.1250   1.0000
  15.000   1.1543   0.09500   0.08795  -0.0501   0.1020   1.0000
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