A review of experimental techniques to predict aircraft spin and recovery characteristics

Malik, Bilal; Masud, Jehanzeb; Akhtar, Shazia

doi:10.1108/aeat-04-2021-0136

Cited by 3 publications

(2 citation statements)

References 26 publications

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“…2 The effects of Reynolds number on post stall and spin characteristics of the aircraft has been extensively studied in literature. [39][40][41] However, in this paper we are focused on the effects of Reynolds number on pre-stall flight characteristics. To illustrate this issue, the aforementioned airfoils are evaluated at two Reynolds numbers, using XFoil.…”

Section: Viscosity Effectsmentioning

confidence: 99%

Toward the feasible solution of a long-lasting dynamic similitude problem

Hajipourzadeh

Banazadeh

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Dynamic similar models are designed to study the flight behavior of the full-scale aircraft in early design stages. Due to physical and operational constraints, full dynamic similarity between the scaled-down model and full-scale aircraft is not feasible. Thus, the scale model would be flying at different Reynolds number and Mach number. A given aircraft configuration with specific aerodynamic characteristics will have different performance if Mach number and Reynolds number are changed considerably, which results in different dynamic behavior of the scale model. To compensate for these dissimilarities, it is proposed to modify the airfoil geometry of the scale model to preserve aerodynamic similarity. In this study, based on the flight regime and design requirements, maximum thickness of the airfoil, maximum camber, and their respective location are modified to preserve aerodynamic characteristics at different Mach and Reynolds numbers. Geometry optimization was performed using Particle Swarm Optimization and the geometry optimization results show that it is possible to mitigate the change in Reynolds and Mach number in various flight conditions. It has been shown that optimized geometries of all test cases had airfoils with lower maximum thickness and slightly higher maximum camber.

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Section: Viscosity Effectsmentioning

confidence: 99%

Toward the feasible solution of a long-lasting dynamic similitude problem

Hajipourzadeh

Banazadeh

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Aircraft spin, as a highly nonlinear and dangerous flight condition, is characterized by a supercritical angle of attack, a large sideslip angle, and a significant yaw rate. Recovering from aircraft spin to avoid ground collisions is a challenging task that has attracted considerable attention [1][2][3][4].…”

Section: Introductionmentioning

confidence: 99%

Fixed-Time Aircraft Spin Recovery Control Based on a Nonsingular Integral Terminal Sliding Mode Approach

Wang,

Zhu

et al. 2024

Applied Sciences

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This paper introduces a control strategy to recover from various spin motions to level trim flight conditions, utilizing a fixed-time nonsingular terminal sliding mode approach to minimize altitude loss. Firstly, an integral terminal sliding mode surface is constructed to guarantee the tracking errors of the spin recovery system converge to the origin within a fixed time and avoid the singularity problem. Next, a fixed-time type reaching law is proposed to weaken the chattering phenomenon and guarantee terminal sliding hyperplanes converge to zero in a fixed time. Furthermore, the stability analysis indicates the fixed-time convergence stability of the spin recovery control system and provides an accurate calculation of the settling time. Finally, comparative simulations are performed to validate the effectiveness and superiority of the developed spin recovery control scheme.

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