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ONERA HOR12 AIRFOIL (hor12-il)

ONERA HOR12 AIRFOIL - Onera propeller blade airfoils from US Patent 4


Airfoil hor12-il
Details Dat file Parser  
(hor12-il) ONERA HOR12 AIRFOIL
Onera propeller blade airfoils from US Patent 4
Max thickness 11.9% at 22.8% chord.
Max camber 3.7% at 46.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
ONERA HOR12 AIRFOIL
       61.       61.

  0.000000  0.000000
  0.002017  0.007742
  0.004025  0.011585
  0.006031  0.014479
  0.010040  0.019218
  0.014047  0.023157
  0.018053  0.026446
  0.022057  0.029286
  0.026652  0.032324
  0.031207  0.035322
  0.035811  0.038040
  0.040465  0.040578
  0.045148  0.043026
  0.049881  0.045374
  0.059457  0.049760
  0.069182  0.053826
  0.079096  0.057592
  0.089110  0.061087
  0.099212  0.064332
  0.109385  0.067327
  0.119596  0.070093
  0.129857  0.072658
  0.140178  0.075023
  0.150548  0.077198
  0.160888  0.079174
  0.171208  0.080989
  0.181567  0.082644
  0.191915  0.084150
  0.202294  0.085505
  0.228448  0.088294
  0.254800  0.090292
  0.280821  0.091542
  0.306691  0.092142
  0.332539  0.092203
  0.358476  0.091733
  0.384282  0.090804
  0.410107  0.089466
  0.435951  0.087757
  0.461815  0.085668
  0.487397  0.083301
  0.513459  0.080652
  0.539211  0.077694
  0.564882  0.074506
  0.590432  0.071099
  0.615902  0.067532
  0.641342  0.063826
  0.666741  0.059979
  0.692081  0.056042
  0.717390  0.052046
  0.742699  0.047990
  0.767958  0.043923
  0.793277  0.039817
  0.818615  0.035631
  0.843914  0.031325
  0.869162  0.026949
  0.894420  0.022532
  0.919688  0.018026
  0.939891  0.014382
  0.960094  0.011187
  0.980297  0.007892
  1.000470  0.004497

  0.000000  0.000000
  0.001983 -0.006801
  0.003974 -0.010454
  0.005968 -0.012808
  0.009958 -0.016415
  0.013950 -0.019123
  0.020779 -0.022517
  0.028659 -0.025124
  0.034272 -0.027016
  0.039876 -0.028669
  0.045430 -0.029981
  0.050935 -0.031053
  0.056400 -0.031995
  0.061826 -0.032807
  0.072568 -0.034051
  0.083141 -0.034925
  0.093545 -0.035509
  0.103840 -0.035882
  0.114055 -0.036086
  0.124190 -0.036129
  0.134285 -0.036042
  0.144331 -0.035845
  0.154327 -0.035559
  0.164274 -0.035182
  0.174240 -0.034735
  0.184227 -0.034218
  0.194183 -0.033621
  0.204150 -0.032954
  0.214067 -0.032238
  0.238691 -0.030295
  0.263114 -0.028322
  0.287857 -0.026290
  0.312761 -0.024068
  0.337175 -0.021636
  0.362509 -0.019125
  0.387464 -0.016514
  0.412408 -0.013862
  0.437323 -0.011221
  0.462217 -0.008669
  0.487401 -0.006258
  0.512105 -0.004096
  0.537108 -0.002224
  0.562200 -0.000613
  0.587402  0.000789
  0.612693  0.002020
  0.638004  0.003091
  0.663354  0.003992
  0.688774  0.004754
  0.714224  0.005395
  0.739683  0.005916
  0.765153  0.006307
  0.790591  0.006489
  0.815999  0.006370
  0.841457  0.005942
  0.866953  0.005264
  0.892440  0.004365
  0.917935  0.003107
  0.938322  0.001791
  0.958718 -0.000255
  0.979114 -0.002391
  0.999530 -0.004497
Dat file parser warnings
  • Line 63 - X value too large but included: 1.000470 0.004497
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Polars for ONERA HOR12 AIRFOIL (hor12-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hor12-il50,000930.7 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hor12-il50,000538 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hor12-il100,000954.7 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hor12-il100,000557.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   hor12-il200,000976.5 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hor12-il200,000576.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hor12-il500,0009103.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   hor12-il500,000597.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hor12-il1,000,0009121.4 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hor12-il1,000,0005108.8 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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