Design, Aerodynamic Optimization Using Pressure Distribution Curve Modification in Fixed-Wing Aerial Vehicle

Norouzi, Pouya; Navabi, M.

doi:10.22034/jtae.2025.9.3.7

Design, Aerodynamic Optimization Using Pressure Distribution Curve Modification in Fixed-Wing Aerial Vehicle

Document Type : Research Article

Authors

Pouya Norouzi ¹

M. Navabi ²

¹ New Technologies Engineering Faculty, Shahid Beheshti University, Tehran, Iran

² Faculty of New Technologies Engineering,, Shahid Beheshti University, Tehran, Iran

10.22034/jtae.2025.9.3.7

Abstract

Fixed-wing aerial vehicles are a class of aeronautical structures in which a rigid, non-moving wing is attached to the fuselage, and flight is enabled through the generation of aerodynamic lift by the wing. Due to their high aerodynamic efficiency and capability for long-range flight, this type of aerial vehicle has received significant attention in studies related to design of flying vehicles. In this study, the design of a fixed-wing aerial vehicle has been presented. To this end, previous researches has been thoroughly reviewed. Based on these evaluations, the primary mission requirements and operational objectives of the designed aerial vehicle have been defined. The design process addresses key issues in aerodynamics and flight dynamics in order to achieve an appropriate and optimized configuration. The optimization efforts include reducing noise in the pressure distribution plots over the airfoil surface and modifying the airfoil through adjustments to the pressure distribution curve. In addition, the effects of changes in tail geometry, as well as variations in the size and placement of the vehicle’s control surfaces, are investigated. Finally various simulations are performed to evaluate the vehicle’s ability to maintain steady, level flight and to assess its maneuvering performance. The dive maneuver, considered one of the most critical flight conditions for this vehicle. Therefore, the vehicle’s capability to recover from a dive and transition smoothly back into level flight is analyzed in detail. The simulation results ultimately confirm the vehicle’s capability to achieve stable straight-and-level flight and satisfactory maneuverability.

Keywords

Aerodynamic Optimization

Pressure Distribution Modification

Six-Degree-of-Freedom Simulation

Mode's Roots Analysis

Fixed-Wing Aerial Vehicle Design

Subjects

Design/System/Reliability/Flight Competence/Flight Testing/...

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