The wing swept angle influence on longitudinal dynamic stability in a combat aircraft configuration

Resumo

© 2024, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.This work proposes an assessment of the delta wing sweep variation of a Generic Future Fighter in the conceptual design phase. Combat aircraft have critical control and therefore the stability analysis of these configurations is compared. Little variation in stability was observed between the 5 different configurations. This indicates that other requirements may become more relevant when designing a fighter aircraft, such as stealth and performance. Thus, this work aims to evaluate the impact of wing sweep on the longitudinal stability of fighter aircraft, considering five different sweep angles: 45°, 47°, 50°, 55°, and 60°. To conduct this analysis, a numerical evaluation, using the Vortex Lattice Method (VLM), wind tunnel results and parameter identification data from past work will be used to obtain the aerodynamic data for each configuration. The aerodynamic data will then be used in a time-domain flight simulation model to analyze the longitudinal stability of the aircraft.