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US1000ROOT (us1000root-il)

US1000ROOT - Great Planes R/C Ultra-Sport 1000 airfoil


Airfoil us1000root-il
Details Dat file Parser  
(us1000root-il) US1000ROOT
Great Planes R/C Ultra-Sport 1000 airfoil
Max thickness 18.6% at 27.1% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  US1000ROOT
 1.000000       0.000048
 0.997540       0.000934
 0.990700       0.003091
 0.980370       0.005675
 0.966980       0.008199
 0.950440       0.010556
 0.930640       0.012925
 0.907750       0.015624
 0.882020       0.018977
 0.853700       0.023180
 0.823090       0.028227
 0.790480       0.033917
 0.756160       0.039949
 0.720430       0.046051
 0.683590       0.052050
 0.645940       0.057871
 0.607780       0.063459
 0.569370       0.068740
 0.530990       0.073629
 0.492650       0.078104
 0.454350       0.082158
 0.416380       0.085731
 0.378870       0.088728
 0.342040       0.090998
 0.306090       0.092399
 0.271200       0.092834
 0.237600       0.092209
 0.205490       0.090384
 0.175040       0.087120
 0.146480       0.082245
 0.119990       0.075919
 0.095760       0.068432
 0.073950       0.059904
 0.054680       0.050077
 0.038110       0.039234
 0.024330       0.028729
 0.013380       0.019477
 0.005480       0.010894
 0.000980       0.003382
 0.000000       0.001306
 0.000980       -.003382
 0.005480       -.010894
 0.013380       -.019477
 0.024330       -.028729
 0.038110       -.039234
 0.054680       -.050077
 0.073950       -.059904
 0.095760       -.068432
 0.119990       -.075919
 0.146480       -.082245
 0.175040       -.087120
 0.205490       -.090384
 0.237600       -.092209
 0.271200       -.092834
 0.306090       -.092399
 0.342040       -.090998
 0.378870       -.088728
 0.416380       -.085731
 0.454350       -.082158
 0.492650       -.078104
 0.530990       -.073629
 0.569370       -.068740
 0.607780       -.063459
 0.645940       -.057871
 0.683590       -.052050
 0.720430       -.046051
 0.756160       -.039949
 0.790480       -.033917
 0.823090       -.028227
 0.853700       -.023180
 0.882020       -.018977
 0.907750       -.015624
 0.930640       -.012925
 0.950440       -.010556
 0.966980       -.008199
 0.980370       -.005675
 0.990700       -.003091
 0.997540       -.000934
 1.000000       -.000048
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Lednicer format dat file
Selig format dat file

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Polars for US1000ROOT (us1000root-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   us1000root-il50,000919 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   us1000root-il50,000524.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   us1000root-il100,000938.3 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   us1000root-il100,000538.6 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   us1000root-il200,000949.1 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   us1000root-il200,000544.3 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   us1000root-il500,000949.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   us1000root-il500,000543.1 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   us1000root-il1,000,000952.3 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   us1000root-il1,000,000545.9 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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