Research on stability for blended-wing-body aircraft
1 School of Aircraft Engineering, Nanchang Hangkong University, Aeroengine.
2 School of Aeronautics, Nanjing University of Aeronautics and Astronautics, Aeroengine.
Research Article
World Journal of Advanced Research and Reviews, 2024, 23(03), 2919–2932
Article DOI: 10.30574/wjarr.2024.23.3.2961
Publication history:
Received on 16 August 2024; revised on 25 September 2024; accepted on 27 September 2024
Abstract:
The primary goal of this research is to research the stability properties of a blended-wing-body (BWB) aircraft. This section examines the assessment and selection of aircraft design parameters, planform design, and reflex wing and conducts a complete aircraft stability analysis. A BWB aircraft conceptual design has been completed and the design. To attain static stability, it was examined and refined. The BWB aircraft's study was performed at three distinct values. The analytical findings were used to calculate the angle-of-attack (AOA) and the stall AOA. We determined the estimated initial departure angle of attack and departure region by assessing the results of the trials and a set of stability criteria.
Keywords:
Blended-Wing-Body Aircraft (BWB); Stall Departure; Static Stability; Dynamic Stability; Stability Modes; Computer-Aided-Design
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Copyright information:
Copyright © 2024 Author(s) retain the copyright of this article. This article is published under the terms of the Creative Commons Attribution Liscense 4.0