p16121: sae aero aircraft design & buildedge.rit.edu/edge/p16121/public/msd ii/p16121 poster rev...

P16121: SAE Aero Aircraft Design & Build

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

Stability and Control The aircraft was designed such that it had cargo-transport aircraft stability and

control characteristics.

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

Left to Right: Ron Manning, Dominic Myren, Marc Protacio, Chris Jones, Matt Zielinski

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.

Performance

Propulsion

The Team

XFLR5 simulation

results displaying lift and

drag distribution during

cruise conditions

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

Concept Selection Many different design concepts were evaluated.

Based on the following selection criteria, the highest rated concept was selected.

Below – Tail Boom

Right – Main Landing Gear

Key Performance CharacteristicsCruise 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

Static thrust test performed

on motor-propeller system to

validate expected aircraft

performance

About 10 pounds maximum

19 inch propeller

Electric motor powered by a

22.2 V, 5000mAh Lithium-

Polymer battery

Power limited to 1000W

Negative Slope:

Necessary for Stability

Negative Slope:

Necessary for StabilityPositive Slope:

Necessary for Stability

Positive Intercept:

Helpful for StabilityIntercept at zero: Symmetric Aircraft

Intercept at zero: Symmetric Aircraft