A Closed-Form, Finite-State Model for the Unsteady Aerodynamics of Rotors

Peters, David A.; He, Cheng Jian; Su, Ay

doi:10.1007/978-3-642-61381-4_405

Cited by 1 publication

(3 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The approximation holds strictly true in the limit of an infinite number of induced flow states. However, it is verified to be a good approximation even for a few-states wake model [8]. Using this approximation, the eigenvalue equation (for cosine states) writes…”

Section: Dynamic Wake Model Eigenvalue Formulationmentioning

confidence: 97%

“…The Generalized Dynamic Wake Model proposed by Peters and He [4,8] is applied to calculate the inflow field induced by rotary blades at the rotor disk. The flight conditions here addressed vary from hover to edgewise flight.…”

Section: The Dynamic Wake Model Formulationmentioning

confidence: 99%

“…Still in the 1980s, David Peters e Chengjian He [4,8] developed a higher-order unsteady wake model known as Peters-He Generalized Dynamic Wake Model. In the Peters-He model, both pressure and induced flow distribution were extended to include higher order harmonics associated with an arbitrary number of radial shape functions.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A Numerical Study of a Rotor Induced Flow Based on a Finite-State Dynamic Wake Model.

Ferreira

Júnior

Gennaro

et al. 2021

TCAM

View full text Add to dashboard Cite

A Helicopter rotor undergoes unsteady aerodynamic loads ruled by the aeroelastic coupling between the elastic blades and the dynamic wake induced by rotary wings. Modeling the dynamic interaction between the structural and aerodynamic fields is a key point to understand aeroelastic phenomena associated with rotor stability, flow induced vibration and noise generation, among others. In this study, we address the Generalized Dynamic Wake Model, which describes the inflow velocity field at the rotor disk as a superposition of a finite number of induced flow states. It is a mature model that has been validated based on experimental data and numerically investigated from an eigenvalue problem formulation, whose eigenvalues and eigenvectors provide a deeper insight on the dynamic wake behavior. The paper extends the results presented in the literature to date in order to support physical interpretation of inflow states drawn from the finite-state wake model for flight conditions varying from hover to edgewise flight. The discussion of the wake model mathematical formulation is also oriented towards practical engineering applications to fill a gap in the literature.

show abstract

Section: Dynamic Wake Model Eigenvalue Formulationmentioning

confidence: 97%

Section: The Dynamic Wake Model Formulationmentioning

confidence: 99%