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ONERA HOR04 AIRFOIL (hor04-il)

ONERA HOR04 AIRFOIL - Onera propeller blade airfoils from US Patent 4


Airfoil hor04-il
Details Dat file Parser  
(hor04-il) ONERA HOR04 AIRFOIL
Onera propeller blade airfoils from US Patent 4
Max thickness 4.1% at 33.2% chord.
Max camber 1.4% at 38.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
ONERA HOR04 AIRFOIL
       60.       51.

  0.000000  0.000000
  0.001417  0.003301
  0.003433  0.005163
  0.005446  0.006562
  0.007460  0.007761
  0.009472  0.008729
  0.012490  0.009935
  0.015507  0.010970
  0.020062  0.012271
  0.025139  0.013430
  0.030236  0.014519
  0.035343  0.015406
  0.040439  0.016294
  0.045545  0.017081
  0.050641  0.017868
  0.060852  0.019241
  0.071074  0.020513
  0.081285  0.021786
  0.091495  0.022908
  0.101716  0.023960
  0.111936  0.024961
  0.122156  0.025892
  0.132376  0.026743
  0.142595  0.027513
  0.152815  0.028233
  0.163044  0.028913
  0.173263  0.029553
  0.183482  0.030142
  0.193711  0.030682
  0.203939  0.031171
  0.229500  0.032202
  0.255060  0.032973
  0.280620  0.033582
  0.306179  0.034112
  0.331728  0.034501
  0.357276  0.034769
  0.383086  0.034966
  0.408843  0.034440
  0.434208  0.033975
  0.459794  0.033500
  0.485409  0.032763
  0.510974  0.031836
  0.536508  0.030758
  0.562001  0.029580
  0.587495  0.028341
  0.618333  0.027366
  0.648468  0.026062
  0.678601  0.024457
  0.708735  0.022952
  0.738868  0.021246
  0.769001  0.019440
  0.799133  0.017634
  0.829266  0.015828
  0.859398  0.013921
  0.889531  0.011914
  0.919663  0.009907
  0.939750  0.008435
  0.959838  0.006963
  0.979926  0.005490
  1.000015  0.004521

  0.000000  0.000000
  0.001396 -0.003189
  0.003401 -0.004602
  0.005408 -0.005262
  0.008389 -0.006005
  0.011432 -0.006447
  0.015449 -0.006771
  0.020471 -0.006989
  0.025494 -0.007146
  0.030517 -0.007222
  0.035540 -0.007229
  0.040563 -0.007215
  0.045586 -0.007211
  0.055632 -0.007264
  0.075724 -0.007430
  0.095816 -0.007496
  0.115909 -0.007461
  0.136002 -0.007326
  0.156094 -0.007291
  0.176187 -0.007156
  0.196280 -0.007121
  0.216372 -0.007086
  0.236465 -0.007051
  0.256557 -0.007016
  0.276650 -0.006981
  0.296744 -0.006545
  0.326884 -0.006141
  0.357024 -0.005536
  0.387165 -0.005031
  0.417305 -0.004427
  0.447446 -0.003621
  0.477588 -0.002815
  0.507729 -0.002009
  0.537870 -0.001204
  0.568011 -0.000599
  0.598152  0.000006
  0.628292  0.000510
  0.658432  0.000914
  0.688571  0.001218
  0.718711  0.001421
  0.748849  0.001423
  0.778988  0.001324
  0.809126  0.001126
  0.839263  0.000726
  0.869400  0.000225
  0.899536 -0.000476
  0.919626 -0.001245
  0.939716 -0.002013
  0.959806 -0.002782
  0.979896 -0.003651
  0.999985 -0.004521
Dat file parser warnings
  • Line 62 - X value too large but included: 1.000015 0.004521
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Polars for ONERA HOR04 AIRFOIL (hor04-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hor04-il50,000928.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hor04-il50,000532.3 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   hor04-il100,000945.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hor04-il100,000540.3 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hor04-il200,000954.8 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hor04-il200,000546.2 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hor04-il500,000961.2 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hor04-il500,000558.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hor04-il1,000,000968.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hor04-il1,000,000570.9 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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