October 28, 2011 Christopher Schumacher (Team Lead) Brian Douglas Christopher Erickson Brad Lester Nathan Love Patrick Mischke Traci Moe Vince Zander

Overview Purpose of Design Project and Requirements Preliminary Design Deliverables Areas of Analysis B+ vs. A Work Qualifications Gantt Chart Summary

Purpose of Design & Requirements Primary Secondary Roll Takeoff Distance: 1028 ft. Climb Gradient: 864 ft/ nmi Roll Landing Distance: 1141 ft. Minimum Full Fuel Payload : 180 lb Similar Loading Flexibility to the SR22 within Approved CG Limits High Speed Cruise Extended Range: 700 nmi Increased Payload: 468 lb with fuel for this mission Design a canard aircraft that is comparable to the SR22 in performance Conduct in-depth analysis on 5 areas of the aircraft Use the analysis to evaluate the preliminary aircraft design

SR22 Design Specifications MediaNewsCirrus-SR22.jpg Wing Area144.9 square ft Wingspan38.5 ft MTOW3400 lb Empty Weight2250 lb Full Fuel Load664 lb Maximum Range+1000 nmi Rate of Climb1400 ft/min Takeoff Distance1020 ft Landing Ground Roll1014 ft Aircraft Length26 ft

Preliminary Design Design Estimates Wing Area145 square ft Wingspan ft MTOW3200 ± 200 lb Empty Weight2000 ± 100 lb Fuel Approximation+550 lb Wing Loading≤ 23.5 lb/ft 2 Range+800 nmi AR8.5 L/D Ratio16 Rate of climb+1304 ft/min

Deliverable Design Groups Integrated Aircraft Design Model Landing Gear Design Wing Configuration Design Control Surface and Loading Stability Design Canard Configuration Design Grades will be based on the depth of research and analysis and not dependent on meeting the requirements

Integrated Aircraft Design Model Using values obtained through initial sizing, construct a CAD model Gather design specifications from individual groups for specific component design Use these specifications to develop an integrated model of the final aircraft

Deliverables: Aircraft Design B+ Work A Work Full exterior CAD design of the original design Full exterior CAD design of the optimized design

Landing Gear Design Process Stability Analysis based on CG and Mounting Locations Determine Loading Cases Tire Selection Stroke Calculations for Landing Gear Damping Initial Size Estimates and Stress Analysis Modeling Finite Element Analysis

Deliverables: Landing Gear B+ Work A Work Design a landing gear system Tire Selection Material Selection Geometry Selection Stress Analysis CAD Model of Landing Gear FEA of one landing gear structure Suggestions for improvement Show how it integrates to the entire design Analyze interactions with rest of aircraft

Wing Configuration Process Select a Main Wing Airfoil and Design Planform Determine All Relevant Aerodynamic Coefficients Analyze Alterations and Customize Airfoil Shape and Size for Performance Optimization Customized Sectioned Wing for Improved Stall Performance whycirrus.com/images/wing.jpg

Deliverables: Wing Configuration B+ Work A Work Design a sectioned wing Fully analyze for : Center of Pressure Moment Coefficient Lift Curve Slope Span Wise Geometry (including wash out analysis)

Controls and Loading Design Process Main goal is developing the process for analyzing weight loading and stability capabilities. Using weights, coefficients of lift, distances, and equations from individual groups to arrange the aircraft design for project requirements. Develop Matlab coding and use ‘ball and stick’ moment and force approximations to conduct analysis.

Deliverables: Controls and Loading B+ Work A Work Calculate Weights and Moments Control Surface Loading Limits Show Loading and Stability Capabilities for Initial Aircraft Design Compare Aircraft Capabilities with FAA Regulations Compare Initial Aircraft with SR22 Capabilities Show Loading and Stability Capabilities for Optimized Aircraft Design Compare Optimized Aircraft Design with SR22 Capabilities

Canard Configuration Process Determine relationship between canard and other aspects of aircraft Manipulate canard sizing to our benefit Analyze flow interactions between the canard and the main wing

Deliverables: Canard Configuration B+ Work A Work Design a Canard Analyze interactions between the canard and wing Calculate forces and moments on the canard Optimize configuration for integrated aircraft Fully Analyze: Center of Pressure Lift Curve Slope Coefficient of Lift

Gantt Chart

Summary Purpose of Design Project and Requirements Preliminary Design Deliverables Areas of Analysis B+ vs. A Work Qualifications Gantt Chart