Year: 2015
Type: conference-paper
Abstract: The aerodynamic model of a generic wing-only airliner configuration is developed for a whole range of angles of attack (−180°. . . +180°), based on experimental data obtained in wind tunnels using static, and forced oscillations. Two different approaches for the tumbling boundaries calculation are used. In the first approach, the steady pitch autorotation is calculated. In the second approach, for various angles of attack, the minimum pitch rate disturbance is considered which can result in tumbling. The tumbling boundaries are calculated via the use of a continuation technique. The dependence of these boundaries on such parameters as flight altitude, aircraft center of gravity position, and total velocity is analyzed.
Authors: A. Khrabrov, M. Sidoryuk
Institution: Central Aerohydrodynamic Institute
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: gold
OpenAlex ID: W830586336