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