Computing Longitudinal Dynamic Derivatives of a VTOL Aircraft Using CFD Simulations and Forced-Oscillation Model

TL;DR

This paper combines CFD simulations and forced oscillation testing to accurately evaluate dynamic aerodynamic derivatives during aircraft transition phases, aiding control and stability design for VTOL and fighter aircraft.

Contribution

It introduces a validated CFD and experimental approach for dynamic derivative estimation during transition phases, enhancing aircraft stability analysis.

Findings

Validated CFD and experimental methods for dynamic derivatives

Insights into unsteady aerodynamics during transition phases

Potential improvements in aircraft control and stability design

Abstract

This study presents a comprehensive evaluation of dynamic aerodynamic derivatives during aircraft transition phases using advanced CFD simulations and forced oscillation testing. Two case studies are examined: a three dimensional fighter aircraft (Standard Dynamic Model, SDM) and a UT24 eVTOL model. The transition phase from vertical hover to forward cruise is analyzed with harmonic oscillation techniques to capture unsteady aerodynamic forces and moments. Grid sensitivity studies and multi zone meshing strategies ensure simulation accuracy, while ANSYS Fluent finite volume solver and coupled pressure velocity algorithms provide high fidelity results. Dynamic derivatives are derived from variations in angle of attack, flight path, and rotational movements, with experimental and numerical data validating the approach. The findings offer valuable insights for robust control design and stability analysis, supporting future advancements in urban air mobility and aerospace engineering. Overall, this approach demonstrates substantial promise for optimizing aircraft performance during critical transition phases. These results pave the way for future innovations