General Aviation Aircraft Conceptual Design

1.0 Overview

Led a semester-long conceptual design of a 4-seat general aviation aircraft meeting range, cruise, and takeoff constraints under FAR Part 23. The work covered every stage from requirements analysis through a validated final configuration and 3D CAD model.

2.0 Constraint sizing

Built a wing loading versus power loading (W/S – W/P) sizing diagram, overlaying the constraints that bound the feasible design space:

• Stall speed limit
• Climb performance requirement
• Landing distance limit
• Takeoff field length

3.0 Aerodynamics and drag buildup

Assembled a component drag buildup rather than assuming a single lumped drag coefficient, accounting for wing parasite and induced drag, fuselage, empennage, landing gear, and interference effects. That model fed the C_L–C_D curves and, through the Breguet range equation, the payload-range trade study.

4.0 Propulsion trade study

Evaluated engine candidates across takeoff, cruise, and climb, downselecting on power-to-weight, fuel efficiency, and certification compatibility. That last one ruled out some otherwise attractive options.

5.0 Stability and control

• Center-of-gravity estimation across loading conditions
• Horizontal and vertical tail sizing
• Scissor plot analysis to confirm static stability
• Controllability verification against FAR Part 23

6.0 Configuration selection

Three configurations were carried far enough to compare on equal terms:

• High-wing conventional: good stability and visibility, higher drag
• Low-wing T-tail (selected): best balance of performance, cabin comfort, and feasibility
• Pusher-prop unconventional: real aerodynamic advantages, but a difficult certification path

The low-wing T-tail was selected for cruise efficiency and a proven Part 23 certification precedent.