Investigating pitching moment stall through dynamic wind tunnel test

Pontillo, Alessandro; Yusuf, Sezsy; Lopez, Guillermo; Rennie, Dominic; Lone, Mudassir

Abstract

Experimental characterisation of aircraft dynamic stall can be a challenging and complex system identification activity. In this article, the authors present a method that combines dynamic wind tunnel testing with parameter estimation techniques to study the nonlinear pitching moment dynamics of a 1/12 scale Hawk model undergoing moment stall. The instrumentation setup allows direct calculation of angular acceleration terms, such as pitch acceleration, and avoids post-processing steps involving differentiation of signals. Data collected from tests, carried out at 20 m/s and 30 m/s, are used for a brief aerodynamic analysis of the observed stall hysteresis. Then an output-error-based parameter estimation process is used to parameterise dynamic stall models and furthermore, illustrate that in a scenario where the model's heave motion is constrained. The observed nonlinear behaviour arises from the nonlinear angle of attack and linear pitch rate components.

• Journal Article Type: Article
• Online Publication Date: Jul 19, 2019
• Publication Date: Feb 28, 2020
• Deposit Date: Apr 22, 2024
• Journal: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
• Print ISSN: 0954-4100
• Electronic ISSN: 2041-3025
• Publisher: SAGE Publications
• Volume: 234
• Issue: 2
• Pages: 267-279
• DOI: https://doi.org/10.1177/0954410019861853
• Public URL: https://uwe-repository.worktribe.com/output/11888250