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ONERA HOR07 AIRFOIL (hor07-il)

ONERA HOR07 AIRFOIL - Onera propeller blade airfoils from US Patent 4


Airfoil hor07-il
Details Dat file Parser  
(hor07-il) ONERA HOR07 AIRFOIL
Onera propeller blade airfoils from US Patent 4
Max thickness 7.2% at 23.2% chord.
Max camber 4.5% at 39.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
ONERA HOR07 AIRFOIL
       45.       56.

  0.000000  0.000000
  0.003773  0.008671
  0.009040  0.014252
  0.014225  0.017769
  0.021437  0.021708
  0.026576  0.024189
  0.032220  0.026756
  0.035803  0.028218
  0.041616  0.030503
  0.046460  0.032340
  0.056549  0.035851
  0.066638  0.039130
  0.074678  0.041625
  0.084785  0.044712
  0.094963  0.047639
  0.105200  0.050404
  0.115476  0.053007
  0.125779  0.054976
  0.136122  0.056935
  0.146511  0.059900
  0.156884  0.061859
  0.167242  0.062810
  0.177626  0.064768
  0.188010  0.066727
  0.198403  0.068685
  0.224553  0.071566
  0.245079  0.073873
  0.295448  0.076422
  0.345806  0.077158
  0.396155  0.076082
  0.446497  0.073697
  0.496832  0.070204
  0.547160  0.065301
  0.597484  0.059491
  0.647803  0.052977
  0.698119  0.045858
  0.748437  0.038941
  0.798755  0.032125
  0.849071  0.025107
  0.899390  0.018492
  0.919517  0.015665
  0.949708  0.011575
  0.969835  0.008848
  0.989963  0.006222
  1.000026  0.004909

  0.000000  0.000000
  0.003168 -0.006372
  0.008110 -0.008896
  0.012996 -0.010423
  0.018026 -0.011457
  0.023057 -0.012199
  0.028090 -0.012770
  0.033123 -0.013109
  0.043191 -0.013667
  0.053261 -0.013922
  0.065345 -0.013987
  0.074410 -0.013855
  0.085490 -0.013441
  0.095565 -0.012740
  0.105640 -0.011887
  0.116108 -0.011188
  0.126315 -0.010216
  0.136482 -0.009213
  0.146608 -0.008200
  0.156705 -0.007166
  0.166802 -0.006123
  0.176918 -0.005070
  0.187015 -0.004006
  0.197102 -0.002922
  0.207179 -0.001828
  0.232209  0.000827
  0.257147  0.003211
  0.295072  0.006532
  0.315223  0.008236
  0.335372  0.009639
  0.355519  0.010437
  0.375665  0.011336
  0.395817  0.013242
  0.426034  0.014086
  0.456252  0.014931
  0.496540  0.015722
  0.526757  0.016566
  0.556969  0.016404
  0.597251  0.016188
  0.627461  0.015723
  0.657670  0.014957
  0.697945  0.013431
  0.728151  0.012161
  0.758355  0.010589
  0.798627  0.008459
  0.828831  0.006685
  0.848965  0.005369
  0.869100  0.004052
  0.899303  0.002178
  0.919436  0.000559
  0.939571 -0.000657
  0.959705 -0.002075
  0.979840 -0.003391
  0.989907 -0.004140
  0.994940 -0.004480
  0.999974 -0.004909
Dat file parser warnings
  • Line 47 - X value too large but included: 1.000026 0.004909
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Polars for ONERA HOR07 AIRFOIL (hor07-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hor07-il50,000943.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hor07-il50,000543.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hor07-il100,000961.1 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   hor07-il100,000559.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hor07-il200,000978.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hor07-il200,000573 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   hor07-il500,000998 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hor07-il500,000580.5 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hor07-il1,000,0009106.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hor07-il1,000,000588.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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