Aircraft Design Analysis Project

Generated from prompt:

Redesign and improve the visual quality of this presentation while keeping ALL original content unchanged. Apply a modern, clean aerospace-themed style with consistent typography, spacing, and hierarchy. Slides to include (same content, improved design): - Cover slide with placeholders for student info and image - Instructions slide (clean layout, callouts, remove clutter) - Section divider slides for Sections 1–3 - Section 1 (3 slides): constraint analysis, TLR interpretation, Class I weight estimation, constraint diagram explanation - Section 2 (3 slides): OpenVSP modelling steps, three-view images, VSPAero results and plots - Section 3 (4 slides): Class II weight estimation, mission fuel analysis, iteration visuals, summary - GenAI declaration slide Design requirements: - Use consistent color palette (dark blue, light blue, white, subtle orange accent) - Improve readability (larger headings, bullet hierarchy, spacing) - Convert dense paragraphs into structured bullets - Add visual placeholders for graphs, diagrams, and screenshots - Use icons for sections (analysis, modelling, results) - Align all elements and use consistent margins - Remove instructional clutter visually but keep text content - Ensure academic/professional look suitable for university submission Do not remove or rewrite any technical content—only improve layout, formatting, and clarity.

This presentation details the iterative aircraft design process, covering constraint analysis, initial sizing, OpenVSP geometry modeling, VSPAero aerodynamics, Class I/II weight estimation, and mission fuel performance verification to meet top-level-

April 15, 202614 slides

Slide 1 of 14

Slide 1 - Aircraft Design Analysis Project

Aircraft Design Analysis Project

Aircraft Design Process: From Constraints to Mission Analysis

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Photo by Navy Medicine on Unsplash

Slide 1 - Aircraft Design Analysis Project

Slide 2 of 14

Slide 2 - Project Instructions & Scope

Focus: Technical analysis of aircraft design using iterative engineering principles.
Constraint Analysis: Evaluate mission requirements against performance bounds.
Modelling: Utilization of OpenVSP for geometric definition and VSPAero for aerodynamics.
Weight Estimation: Applying Class I and Class II methods for accurate mass properties.
Outcome: Comprehensive design summary and mission fuel performance evaluation.

Slide 3 of 14

Slide 3 - Section 1

Constraint Analysis & Initial Design

Foundations for performance and configuration sizing

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Slide 4 of 14

Slide 4 - 1.1 Constraint Analysis & TLR

Define the design space using Top Level Requirements (TLR).
Key parameters: Takeoff weight, wing loading, and power loading.
Performance constraints: Stall speed, cruise speed, climb rate, and range.
Objective: Identify the feasible design region bounded by mission specs.

Slide 5 of 14

Slide 5 - 1.2 Constraint Diagram Analysis

The constraint diagram visualizes performance boundaries.
Feasible design space lies in the intersection of requirement curves.
Identifies optimal design point (minimum wing and power loading).

Slide 6 of 14

Slide 6 - 1.3 Class I Weight Estimation

1.5T: MTOM
0.85: W/S Ratio
0.12: P/W Ratio

Slide 7 of 14

Slide 7 - Section 2

Geometry Modelling & Aerodynamics

OpenVSP configuration and VSPAero validation

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Photo by Codioful (Formerly Gradienta) on Unsplash

Slide 8 of 14

Slide 8 - 2.1 OpenVSP Modelling Process

Step	Process Description
1. Geometry Creation	Define airfoils, wing planform, and fuselage lofting.
2. Meshing	Set up surface panels for VSPAero solver.
3. Analysis Execution	Run sweep tests across angle of attack range.
4. Result Extraction	Collect lift and drag coefficients (CL, CD).