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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.87 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e174-il-1000000.txt
Download as CSV file: xf-e174-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E174  (Dicke 8.92%)                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3439   0.08714   0.08559  -0.0317   1.0000   0.0088
  -8.250  -0.3504   0.08233   0.08082  -0.0332   1.0000   0.0091
  -8.000  -0.3492   0.07939   0.07791  -0.0340   1.0000   0.0091
  -7.750  -0.3452   0.07628   0.07482  -0.0358   0.9871   0.0092
  -7.500  -0.3112   0.07044   0.06894  -0.0475   0.9591   0.0094
  -7.250  -0.2851   0.06556   0.06392  -0.0566   0.9090   0.0097
  -7.000  -0.2807   0.06152   0.05968  -0.0603   0.8632   0.0097
  -6.750  -0.2726   0.05735   0.05538  -0.0643   0.8343   0.0098
  -6.500  -0.2612   0.05270   0.05059  -0.0687   0.8128   0.0100
  -6.250  -0.2467   0.04757   0.04530  -0.0732   0.7954   0.0102
  -6.000  -0.2297   0.04208   0.03962  -0.0770   0.7807   0.0105
  -5.750  -0.2109   0.03624   0.03352  -0.0800   0.7680   0.0110
  -5.500  -0.1866   0.02981   0.02667  -0.0814   0.7570   0.0123
  -5.250  -0.1649   0.02592   0.02231  -0.0822   0.7466   0.0124
  -4.500  -0.0962   0.01392   0.00885  -0.0826   0.7198   0.0110
  -4.250  -0.0694   0.01253   0.00717  -0.0823   0.7113   0.0109
  -4.000  -0.0422   0.01144   0.00589  -0.0821   0.7034   0.0108
  -3.750  -0.0150   0.01070   0.00499  -0.0819   0.6957   0.0109
  -3.500   0.0127   0.01020   0.00439  -0.0818   0.6883   0.0114
  -3.250   0.0401   0.00962   0.00369  -0.0817   0.6814   0.0115
  -3.000   0.0679   0.00907   0.00306  -0.0816   0.6747   0.0115
  -2.750   0.0956   0.00869   0.00258  -0.0815   0.6682   0.0118
  -2.500   0.1238   0.00841   0.00222  -0.0814   0.6620   0.0123
  -2.250   0.1518   0.00803   0.00175  -0.0814   0.6559   0.0140
  -2.000   0.1800   0.00786   0.00153  -0.0813   0.6502   0.0161
  -1.750   0.2082   0.00762   0.00132  -0.0813   0.6442   0.0309
  -1.500   0.2358   0.00730   0.00120  -0.0814   0.6386   0.0988
  -1.250   0.2638   0.00706   0.00113  -0.0816   0.6332   0.1571
  -1.000   0.2916   0.00680   0.00108  -0.0817   0.6276   0.2394
  -0.750   0.3191   0.00652   0.00106  -0.0818   0.6224   0.3424
  -0.500   0.3465   0.00612   0.00106  -0.0819   0.6171   0.4889
  -0.250   0.3735   0.00582   0.00108  -0.0819   0.6117   0.6124
   0.000   0.3990   0.00545   0.00112  -0.0814   0.6068   0.7647
   0.250   0.4207   0.00500   0.00115  -0.0796   0.6016   0.9549
   0.500   0.4579   0.00503   0.00112  -0.0816   0.5961   1.0000
   0.750   0.4860   0.00507   0.00112  -0.0816   0.5910   1.0000
   1.000   0.5141   0.00513   0.00113  -0.0816   0.5854   1.0000
   1.250   0.5419   0.00521   0.00115  -0.0816   0.5799   1.0000
   1.500   0.5701   0.00525   0.00117  -0.0817   0.5740   1.0000
   1.750   0.5979   0.00533   0.00120  -0.0816   0.5675   1.0000
   2.000   0.6260   0.00538   0.00124  -0.0817   0.5607   1.0000
   2.250   0.6538   0.00547   0.00128  -0.0817   0.5534   1.0000
   2.500   0.6818   0.00553   0.00132  -0.0817   0.5462   1.0000
   2.750   0.7095   0.00562   0.00139  -0.0817   0.5387   1.0000
   3.000   0.7375   0.00568   0.00145  -0.0817   0.5313   1.0000
   3.250   0.7650   0.00579   0.00151  -0.0817   0.5234   1.0000
   3.500   0.7930   0.00586   0.00159  -0.0817   0.5147   1.0000
   3.750   0.8205   0.00596   0.00168  -0.0817   0.5057   1.0000
   4.000   0.8480   0.00608   0.00177  -0.0816   0.4957   1.0000
   4.250   0.8755   0.00619   0.00187  -0.0816   0.4836   1.0000
   4.500   0.9023   0.00636   0.00197  -0.0815   0.4639   1.0000
   4.750   0.9285   0.00661   0.00212  -0.0813   0.4335   1.0000
   5.000   0.9545   0.00688   0.00229  -0.0811   0.4039   1.0000
   5.250   0.9796   0.00726   0.00252  -0.0808   0.3659   1.0000
   5.500   1.0027   0.00790   0.00287  -0.0802   0.3042   1.0000
   5.750   1.0236   0.00880   0.00338  -0.0794   0.2287   1.0000
   6.000   1.0452   0.00958   0.00387  -0.0787   0.1701   1.0000
   6.250   1.0666   0.01037   0.00438  -0.0780   0.1179   1.0000
   6.500   1.0870   0.01125   0.00496  -0.0771   0.0672   1.0000
   6.750   1.1050   0.01237   0.00576  -0.0758   0.0172   1.0000
   7.000   1.1282   0.01288   0.00626  -0.0752   0.0124   1.0000
   7.250   1.1514   0.01338   0.00680  -0.0745   0.0108   1.0000
   7.500   1.1741   0.01389   0.00737  -0.0738   0.0100   1.0000
   7.750   1.1968   0.01438   0.00793  -0.0731   0.0095   1.0000
   8.000   1.2187   0.01493   0.00854  -0.0723   0.0092   1.0000
   8.250   1.2398   0.01553   0.00920  -0.0714   0.0089   1.0000
   8.500   1.2601   0.01618   0.00991  -0.0704   0.0086   1.0000
   8.750   1.2792   0.01688   0.01068  -0.0692   0.0084   1.0000
   9.000   1.2971   0.01766   0.01153  -0.0679   0.0081   1.0000
   9.250   1.3131   0.01852   0.01246  -0.0663   0.0078   1.0000
   9.500   1.3265   0.01952   0.01355  -0.0644   0.0076   1.0000
   9.750   1.3338   0.02083   0.01495  -0.0617   0.0074   1.0000
  10.000   1.3343   0.02225   0.01647  -0.0578   0.0072   1.0000
  10.250   1.3325   0.02399   0.01832  -0.0541   0.0071   1.0000
  10.500   1.3331   0.02591   0.02034  -0.0511   0.0070   1.0000
  10.750   1.3483   0.02643   0.02094  -0.0499   0.0068   1.0000
  11.000   1.3559   0.02781   0.02241  -0.0481   0.0067   1.0000
  11.250   1.3650   0.02908   0.02378  -0.0466   0.0066   1.0000
  11.500   1.3707   0.03084   0.02564  -0.0450   0.0065   1.0000
  11.750   1.3769   0.03263   0.02753  -0.0435   0.0065   1.0000
  12.000   1.3824   0.03458   0.02960  -0.0422   0.0064   1.0000
  12.250   1.3879   0.03658   0.03171  -0.0411   0.0063   1.0000
  12.500   1.3920   0.03879   0.03406  -0.0400   0.0062   1.0000
  12.750   1.3944   0.04138   0.03679  -0.0389   0.0062   1.0000
  13.000   1.3958   0.04404   0.03960  -0.0381   0.0062   1.0000
  13.250   1.3973   0.04660   0.04229  -0.0376   0.0060   1.0000
  13.500   1.3956   0.04974   0.04559  -0.0372   0.0060   1.0000
  13.750   1.3912   0.05338   0.04940  -0.0369   0.0060   1.0000
  14.000   1.3872   0.05686   0.05303  -0.0371   0.0059   1.0000
  14.250   1.3777   0.06138   0.05775  -0.0375   0.0060   1.0000
  14.500   1.3693   0.06576   0.06230  -0.0383   0.0059   1.0000
  14.750   1.3589   0.07066   0.06737  -0.0396   0.0059   1.0000
  15.000   1.3461   0.07621   0.07310  -0.0414   0.0059   1.0000
  15.250   1.3344   0.08183   0.07888  -0.0436   0.0058   1.0000
  15.500   1.3193   0.08837   0.08559  -0.0464   0.0058   1.0000
  15.750   1.3016   0.09581   0.09321  -0.0499   0.0058   1.0000
  16.000   1.2849   0.10345   0.10101  -0.0540   0.0058   1.0000
  16.250   1.2680   0.11153   0.10926  -0.0585   0.0058   1.0000
  16.500   1.2460   0.12134   0.11924  -0.0642   0.0059   1.0000
  16.750   1.2249   0.13152   0.12957  -0.0705   0.0060   1.0000
  17.000   1.2007   0.14320   0.14142  -0.0779   0.0061   1.0000
  17.250   1.1777   0.15544   0.15380  -0.0857   0.0062   1.0000
  17.500   1.1496   0.17035   0.16885  -0.0951   0.0065   1.0000
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