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ONERA HOR20 AIRFOIL (hor20-il)

ONERA HOR20 AIRFOIL - Onera propeller blade airfoils from US Patent 4


Airfoil hor20-il
Details Dat file Parser  
(hor20-il) ONERA HOR20 AIRFOIL
Onera propeller blade airfoils from US Patent 4
Max thickness 20.4% at 24.3% chord.
Max camber 3.3% at 51.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
ONERA HOR20 AIRFOIL
       57.       61.

  0.000000  0.000000
  0.001989  0.010702
  0.004981  0.019205
  0.006977  0.023207
  0.009972  0.028310
  0.014965  0.035315
  0.019959  0.040920
  0.024954  0.046125
  0.029949  0.050830
  0.041290  0.060361
  0.054900  0.070185
  0.064294  0.075984
  0.073949  0.081294
  0.083804  0.086184
  0.093819  0.090674
  0.103955  0.094814
  0.114181  0.098584
  0.124498  0.102044
  0.134905  0.105225
  0.145392  0.108105
  0.155869  0.110716
  0.166317  0.113066
  0.176805  0.115197
  0.187293  0.117077
  0.197821  0.118748
  0.224508  0.122085
  0.251396  0.124331
  0.278104  0.125578
  0.304334  0.125874
  0.330505  0.125361
  0.356836  0.124117
  0.383018  0.122213
  0.409170  0.119739
  0.435353  0.116755
  0.461587  0.113292
  0.487451  0.109457
  0.513675  0.105454
  0.539969  0.101100
  0.565924  0.096486
  0.591748  0.091642
  0.617383  0.086607
  0.642939  0.081423
  0.668454  0.076108
  0.693859  0.070684
  0.719185  0.065209
  0.744480  0.059684
  0.769746  0.054150
  0.795041  0.048655
  0.820397  0.043180
  0.845732  0.037666
  0.870978  0.032111
  0.896183  0.026546
  0.921439  0.021031
  0.941633  0.016552
  0.961848  0.012362
  0.979991  0.008880
  0.999996  0.004500

  0.000000  0.000000
  0.002019 -0.018998
  0.005026 -0.026395
  0.010034 -0.034490
  0.015040 -0.040285
  0.020045 -0.044880
  0.025049 -0.048775
  0.030052 -0.052370
  0.036936 -0.056383
  0.042910 -0.059677
  0.048822 -0.062411
  0.054625 -0.064745
  0.060357 -0.066870
  0.066039 -0.068784
  0.077242 -0.072003
  0.088165 -0.074582
  0.098837 -0.076681
  0.109308 -0.078391
  0.119620 -0.079770
  0.129801 -0.080870
  0.139902 -0.081700
  0.149912 -0.082310
  0.159823 -0.082730
  0.169663 -0.082980
  0.179513 -0.083060
  0.189393 -0.082981
  0.199233 -0.082751
  0.209072 -0.082381
  0.218872 -0.081881
  0.243000 -0.080217
  0.266928 -0.078193
  0.291036 -0.075879
  0.315623 -0.073114
  0.340270 -0.069870
  0.364746 -0.066315
  0.389392 -0.062481
  0.414058 -0.058426
  0.438694 -0.054241
  0.463280 -0.050017
  0.488236 -0.045872
  0.512832 -0.041837
  0.537358 -0.038123
  0.562225 -0.034708
  0.587222 -0.031523
  0.612409 -0.028518
  0.637686 -0.025692
  0.662993 -0.023027
  0.688401 -0.020532
  0.713898 -0.018186
  0.739436 -0.015971
  0.764984 -0.013905
  0.790522 -0.012069
  0.815991 -0.010554
  0.841479 -0.009419
  0.867049 -0.008623
  0.892668 -0.008087
  0.910007 -0.007290
  0.930007 -0.006770
  0.950006 -0.006100
  0.970005 -0.005480
  1.000004 -0.004500
Dat file parser warnings
  • Line 120 - X value too large but included: 1.000004 -0.004500
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Polars for ONERA HOR20 AIRFOIL (hor20-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hor20-il50,00094.1 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hor20-il50,000521.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   hor20-il100,000934.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hor20-il100,000544.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hor20-il200,000961.6 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hor20-il200,000563.4 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hor20-il500,000991.1 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hor20-il500,000583.9 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   hor20-il1,000,0009112.4 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hor20-il1,000,000599.9 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
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