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ONERA HOR20 AIRFOIL (hor20-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR20 AIRFOIL (hor20-il)
Reynolds number: 100,000
Max Cl/Cd: 34.35 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor20-il-100000.txt
Download as CSV file: xf-hor20-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR20 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2009   0.10512   0.09995  -0.0329   0.9874   0.2496
  -8.250  -0.1726   0.10143   0.09622  -0.0382   0.9746   0.2565
  -8.000  -0.5071   0.04043   0.03372  -0.0906   0.9372   0.2097
  -7.750  -0.4649   0.04011   0.03352  -0.0923   0.9264   0.2140
  -7.500  -0.4279   0.04065   0.03419  -0.0923   0.9123   0.2182
  -7.250  -0.4224   0.03578   0.02858  -0.0956   0.8974   0.2271
  -7.000  -0.3891   0.03607   0.02910  -0.0947   0.8851   0.2309
  -6.750  -0.3634   0.03612   0.02921  -0.0937   0.8698   0.2358
  -6.500  -0.3482   0.03337   0.02587  -0.0947   0.8577   0.2445
  -6.250  -0.3219   0.03346   0.02616  -0.0933   0.8435   0.2486
  -6.000  -0.2965   0.03336   0.02608  -0.0923   0.8313   0.2543
  -5.750  -0.2768   0.03146   0.02370  -0.0929   0.8187   0.2631
  -5.500  -0.2507   0.03153   0.02394  -0.0916   0.8070   0.2677
  -5.250  -0.2252   0.03133   0.02372  -0.0908   0.7948   0.2742
  -5.000  -0.2016   0.03004   0.02207  -0.0911   0.7849   0.2829
  -4.750  -0.1752   0.03018   0.02237  -0.0901   0.7725   0.2881
  -4.500  -0.1490   0.02989   0.02194  -0.0893   0.7640   0.2955
  -4.250  -0.1232   0.02914   0.02104  -0.0899   0.7516   0.3037
  -4.000  -0.0963   0.02925   0.02123  -0.0888   0.7425   0.3094
  -3.750  -0.0693   0.02893   0.02076  -0.0889   0.7329   0.3180
  -3.500  -0.0425   0.02855   0.02033  -0.0887   0.7226   0.3252
  -3.250  -0.0150   0.02860   0.02037  -0.0878   0.7152   0.3318
  -3.000   0.0129   0.02821   0.01977  -0.0886   0.7051   0.3419
  -2.750   0.0398   0.02816   0.01983  -0.0879   0.6962   0.3476
  -2.500   0.0678   0.02815   0.01974  -0.0871   0.6896   0.3550
  -2.250   0.0959   0.02783   0.01927  -0.0880   0.6795   0.3649
  -2.000   0.1230   0.02790   0.01945  -0.0873   0.6715   0.3707
  -1.750   0.1517   0.02783   0.01927  -0.0868   0.6654   0.3791
  -1.500   0.1795   0.02767   0.01905  -0.0874   0.6559   0.3881
  -1.250   0.2068   0.02776   0.01922  -0.0868   0.6480   0.3946
  -1.000   0.2361   0.02760   0.01891  -0.0866   0.6421   0.4039
  -0.750   0.2636   0.02761   0.01891  -0.0869   0.6337   0.4120
  -0.500   0.2907   0.02771   0.01908  -0.0865   0.6255   0.4192
  -0.250   0.3209   0.02750   0.01867  -0.0866   0.6194   0.4298
   0.000   0.3479   0.02760   0.01883  -0.0864   0.6122   0.4372
   0.250   0.3747   0.02777   0.01905  -0.0862   0.6037   0.4461
   0.500   0.4047   0.02756   0.01868  -0.0863   0.5974   0.4569
   0.750   0.4327   0.02763   0.01876  -0.0858   0.5918   0.4654
   1.000   0.4593   0.02792   0.01906  -0.0862   0.5828   0.4772
   1.250   0.4868   0.02782   0.01901  -0.0857   0.5762   0.4859
   1.500   0.5177   0.02773   0.01875  -0.0857   0.5712   0.4989
   1.750   0.5415   0.02809   0.01928  -0.0853   0.5630   0.5084
   2.000   0.5694   0.02820   0.01936  -0.0853   0.5557   0.5216
   2.250   0.5984   0.02801   0.01915  -0.0849   0.5504   0.5328
   2.500   0.6259   0.02833   0.01942  -0.0850   0.5441   0.5468
   2.750   0.6493   0.02860   0.01989  -0.0844   0.5360   0.5576
   3.000   0.6789   0.02852   0.01973  -0.0843   0.5301   0.5715
   3.250   0.7093   0.02841   0.01954  -0.0840   0.5255   0.5848
   3.500   0.7295   0.02913   0.02047  -0.0836   0.5169   0.5969
   3.750   0.7564   0.02923   0.02060  -0.0832   0.5103   0.6106
   4.000   0.7870   0.02905   0.02035  -0.0830   0.5054   0.6239
   4.250   0.8098   0.02974   0.02113  -0.0826   0.4984   0.6379
   4.500   0.8321   0.03015   0.02171  -0.0818   0.4909   0.6510
   4.750   0.8619   0.03006   0.02157  -0.0817   0.4855   0.6668
   5.000   0.8927   0.03007   0.02150  -0.0815   0.4807   0.6839
   5.250   0.9066   0.03113   0.02287  -0.0802   0.4718   0.6985
   5.500   0.9339   0.03117   0.02295  -0.0798   0.4658   0.7184
   5.750   0.9660   0.03086   0.02259  -0.0795   0.4613   0.7439
   6.000   0.9785   0.03196   0.02401  -0.0779   0.4534   0.7729
   6.250   0.9973   0.03208   0.02440  -0.0761   0.4470   0.8278
   6.500   1.0353   0.03156   0.02388  -0.0771   0.4420   1.0000
   6.750   1.0597   0.03255   0.02481  -0.0775   0.4356   1.0000
   7.000   1.0778   0.03367   0.02597  -0.0769   0.4280   1.0000
   7.250   1.1109   0.03365   0.02578  -0.0773   0.4229   1.0000
   7.500   1.1501   0.03348   0.02532  -0.0782   0.4189   1.0000
   7.750   1.1465   0.03585   0.02802  -0.0755   0.4102   1.0000
   8.000   1.1744   0.03603   0.02812  -0.0753   0.4045   1.0000
   8.250   1.2148   0.03550   0.02735  -0.0760   0.4002   1.0000
   8.500   1.2131   0.03776   0.02985  -0.0734   0.3928   1.0000
   8.750   1.2306   0.03858   0.03069  -0.0723   0.3865   1.0000
   9.000   1.2702   0.03801   0.02993  -0.0729   0.3821   1.0000
   9.250   1.2848   0.03923   0.03120  -0.0716   0.3765   1.0000
   9.500   1.2750   0.04171   0.03390  -0.0682   0.3693   1.0000
   9.750   1.3108   0.04131   0.03338  -0.0685   0.3645   1.0000
  10.000   1.3662   0.04012   0.03190  -0.0705   0.3606   1.0000
  10.250   1.2966   0.04587   0.03819  -0.0623   0.3531   1.0000
  10.500   1.3106   0.04663   0.03894  -0.0608   0.3477   1.0000
  10.750   1.3923   0.04375   0.03575  -0.0646   0.3435   1.0000
  11.000   1.0640   0.07826   0.07116  -0.0589   0.3235   1.0000
  11.250   1.1265   0.07263   0.06546  -0.0563   0.3233   1.0000
  11.500   1.2009   0.06615   0.05888  -0.0540   0.3228   1.0000
  11.750   1.3147   0.05684   0.04935  -0.0527   0.3220   1.0000
  12.750   0.8359   0.14334   0.13665  -0.0792   0.2703   1.0000
  13.000   0.8170   0.15103   0.14440  -0.0827   0.2694   1.0000
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