P16121: SAE Aero Aircraft Design & Buildedge.rit.edu/edge/P16121/public/MSD II/P16121 Poster Rev...
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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 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 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 Stability Positive Slope: Necessary for Stability Positive Intercept: Helpful for Stability Intercept at zero: Symmetric Aircraft Intercept at zero: Symmetric Aircraft
Transcript of 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
