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ARA-D 10% AIRFOIL (arad10-il)

ARA-D 10% AIRFOIL - Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 10% thick propeller airfoil


Airfoil arad10-il
Details Dat file Parser  
(arad10-il) ARA-D 10% AIRFOIL
Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 10% thick propeller airfoil
Max thickness 10% at 25% chord.
Max camber 4% at 35% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 ARA-D 10% AIRFOIL
26.        26.
 
 0.00000   0.00000
  .00300    .013713
  .01000    .025227
  .02000    .035554
  .04000    .049237
  .07000    .062305
  .10000    .070856
  .15000    .079585
  .20000    .084614
  .25000    .087500
  .30000    .088908
  .35000    .088961
  .40000    .087685
  .45000    .085232
  .50000    .081734
  .55000    .077289
  .60000    .072014
  .65000    .066012
  .70000    .059363
  .75000    .052101
  .80000    .044232
  .85000    .035756
  .90000    .026692
  .95000    .017146
  .97500    .012327
 1.00000    .007500
 
 0.00000   0.00000
  .00300   -.007388
  .01000   -.012555
  .02000   -.016369
  .04000   -.020033
  .07000   -.021626
  .10000   -.021088
  .15000   -.018291
  .20000   -.015159
  .25000   -.012500
  .30000   -.010571
  .35000   -.009175
  .40000   -.008108
  .45000   -.007304
  .50000   -.006734
  .55000   -.006377
  .60000   -.006214
  .65000   -.006227
  .70000   -.006399
  .75000   -.006673
  .80000   -.006965
  .85000   -.007181
  .90000   -.007282
  .95000   -.007282
  .97500   -.007338
 1.00000   -.007500
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Lednicer format dat file
Selig format dat file

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Polars for ARA-D 10% AIRFOIL (arad10-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   arad10-il50,000934.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   arad10-il50,000536.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   arad10-il100,000951.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   arad10-il100,000549.5 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   arad10-il200,000966.2 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   arad10-il200,000561.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   arad10-il500,000982.1 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   arad10-il500,000582.3 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   arad10-il1,000,0009100.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   arad10-il1,000,000598.7 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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