Helicopter blade flapping with and without small angle assumption in the presence of dynamic stall

DOI10.1016/j.apm.2010.02.010zbMath1201.76099OpenAlexW2053450260MaRDI QIDQ611634

Jyoti Ranjan Majhi, Ranjan Ganguly

Publication date: 14 December 2010

Published in: Applied Mathematical Modelling (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1016/j.apm.2010.02.010

zbMATH Keywords

aeroelasticityhelicopteraerodynamicsdynamic stallflapping

Mathematics Subject Classification ID

Fluid-solid interactions (including aero- and hydro-elasticity, porosity, etc.) (74F10) General aerodynamics and subsonic flows (76G25)

Related Items (5)

Robust hierarchical control of a laboratory helicopter ⋮ FLIGHT LIMITATIONS IMPOSED ON SINGLE ROTOR AND COAXIAL HELICOPTERS BY THE LIFT EQUATION ⋮ Effect of the wing shape on the thrust of flapping wing ⋮ On the flapping motion of a helicopter blade ⋮ A transfer matrix method capable of determining the exact solutions of a twisted Bernoulli-Euler beam with multiple edge cracks

Cites Work

• Unnamed Item
• A semi-analytic approach for the nonlinear dynamic response of circular plates
• Assessment of an Eulerian CFD model for prediction of dilute droplet dispersion in a turbulent jet
• Asymptotic treatment of the trapeze effect in finite element cross-sectional analysis of composite beams
• Implications of cubic physical/aerodynamic non-linearities on the character of the flutter instability boundary
• Non-linear viscoelastodynamic equations of three-dimensional rotating structures in finite displacement and finite element discretization
• Stability of continuous Runge-Kutta-type methods for nonlinear neutral delay-differential equations
• Computational aero-acoustic analysis of a passenger car with a rear spoiler
• Dynamic motion of whirling rods with Coriolis effect
• Dynamic response of a rotating ball screw subject to a moving regenerative force in grinding
• Explicit Runge-Kutta pairs appropriate for engineering applications
• Nonlinear flutter of a buckled shear-deformable composite panel in a high-supersonic flow

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