1. Key Performance Characteristics
P16121: SAE Aero Aircraft Design & Build
Objective
To design, build, and test an aircraft for the Regular Class of the 2016 SAE Aero Design Competition. The aircraft serves as a development platform for the RIT Aero Design Club so that they may competitively participate in future competitions.
Concept Selection
Many different design concepts were evaluated.
Based on the following selection criteria, the highest rated concept was selected.
Aerodynamics
XFLR5 was the primary aerodynamics computational software utilized (Vortex-Lattice Method)
ANSYS FLUENT (Navier-Stokes+Spalart Allmaras) was used to verify XFLR5 results through horizontal stabilizer analysis
XFLR5 simulation results displaying lift and drag distribution during cruise conditions
Structural Design and Stress Analysis
All load bearing structures are metallic to ensure structural integrity
Aluminum chassis designed such that loads are transferred to spars during flight, and landing gear bear loads on ground and endure landing impact
Stress analysis performed for worst-case loading scenarios on all metallic parts
Below – Tail Boom
Right – Main Landing Gear
Propulsion
Static thrust test performed on motor-propeller system to validate expected aircraft performance
About 10 pounds maximum
18 inch propeller
Electric motor powered by a 22.4 V, 5000mAh lithium-ion battery
Power limited to 1000W
Performance
Key Performance Characteristics
Cruise Lift Coefficient
1.075
Cruise Drag Coefficient
0.087
Cruise Pitching Moment Coefficient
0.005
Maximum Lifting Capacity
30.0 lbf
Drag Force During Cruise
3.4 lbf
Thrust Available During Cruise
>5.0 lbf
Thrust Required for Take-Off
≈10 lbf
Take-Off Distance
190.1 ft
Landing Distance
307.2 ft
Stall Velocity
40.9 ft/s
Take-Off Velocity
49.1 ft/s
Cruise Velocity
55.7 ft/s
Landing Velocity
53.1 ft/s
Acknowledgements
Dr. Kolodziej for project completion guidance
Mike Walker for guidance in Design Project Leadership
Professor Wellin for static thrust test assistance
RIT Aero Design Club for manufacturing assistance
Dr. Venkataraman for aircraft design input
Boeing for generous financial contributions
Stability and Control
The aircraft was designed such that it had cargo-transport aircraft stability and control characteristics.
The Team
Left to Right: Ron Manning, Dominic Myren, Marc Protacio, Chris Jones, Matt Zielinski