Overview
The project goal is to analyze and recreate an airfoil based on the
NACA number. Then test and record the airfoil in simulated conditions. Then
create an airfoil and test it to see if it matched the characteristics of its
simulated counterparts.
AT-501
Facts
The airfoil chosen comes from the Airtractor AT-501, with a NACA number
of 4415.The Airtractor AT-501 is use for agricultural crop dusting, it is made
by Airtractor inc and it is a monoplane low wing taildragger (see picture
above).
Airfoil
Data
Getting the vital data based on the NACA number involved looking up the
NACA number for the chosen airfoil, and plotting its profile. We used the NACA 4
digit series profile generate to get the profile. This profile is used to create
the airfoil for testing.
Airfoil Simulation
The NASA FoilSim applet calculates the lift of an airfoil based on user
inputs of flow conditions and wing geometry. We used the NACA number (4415) to
set the shape of the airfoil. The first number (4) represents the camber, the
last two digits (15) represents the thickness. The size of the simulate airfoil
is the same as the test airfoil (4" chord and 4" span). The flight conditions
are set at 60 mph and the altitude is at 0. The data is recorded with the
Angle of Attack is set to -20 and
the Final Angle of Attack to 20 and the Angle of Attack Step to 5 degrees.
Complete Foilsim Excel chart is below.
The project goal is to analyze and recreate an airfoil based on the
NACA number. Then test and record the airfoil in simulated conditions. Then
create an airfoil and test it to see if it matched the characteristics of its
simulated counterparts.
AT-501
Facts
The airfoil chosen comes from the Airtractor AT-501, with a NACA number
of 4415.The Airtractor AT-501 is use for agricultural crop dusting, it is made
by Airtractor inc and it is a monoplane low wing taildragger (see picture
above).
Airfoil
Data
Getting the vital data based on the NACA number involved looking up the
NACA number for the chosen airfoil, and plotting its profile. We used the NACA 4
digit series profile generate to get the profile. This profile is used to create
the airfoil for testing.
Airfoil Simulation
The NASA FoilSim applet calculates the lift of an airfoil based on user
inputs of flow conditions and wing geometry. We used the NACA number (4415) to
set the shape of the airfoil. The first number (4) represents the camber, the
last two digits (15) represents the thickness. The size of the simulate airfoil
is the same as the test airfoil (4" chord and 4" span). The flight conditions
are set at 60 mph and the altitude is at 0. The data is recorded with the
Angle of Attack is set to -20 and
the Final Angle of Attack to 20 and the Angle of Attack Step to 5 degrees.
Complete Foilsim Excel chart is below.