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Yihua Cao, Jifei Wang, Yuan-An Su (2003)
Mixed Jameson/Total-VariationDiminishing Scheme Applied to Simulating Rotor Airfoil FlowfieldJournal of Aircraft, 40
J.E. Fairchild, N.N. Batra, R.L. Stewart
Influence of design parameters on fan‐in‐fin static performance
M. Vialle, G. Arnaud
A new generation of fenestron fan‐in‐fin tail rotor on EC 135
B. Baldwin, H. Lomax (1978)
Thin-layer approximation and algebraic model for separated turbulent flows
S. Davis, I. Chang (1986)
The Critical Role of Computational Fluid Dynamics in Rotary-Wing Aerodynamics
I. Abbott, A. Doenhoff, L. Stivers (1945)
Summary of Airfoil Data
A. Jameson, W. Schmidt, Eli Turkel (1981)
Numerical solution of the Euler equations by finite volume methods using Runge Kutta time stepping schemes
J. Wang, G. Widhopf (1987)
A high-resolution TVD finite volume scheme for the Euler equations in conservation formJournal of Computational Physics, 84
Purpose – To establish a method for the calculations in the field of rotor aerodynamics. Design/methodology/approach – The calculations of the lift‐drag characteristics of OAF and NACA63A312 airfoils at low speed are made using Jameson/TVD mixed scheme. By means of finite volume approach for numerical discretization and Runge‐Kutta time‐stepping advance, Euler/Navier‐Stokes equations are solved. Furthermore, a model based on circular tiny segment momentum theory and blade element theory is established to study the thrust and power of ducted tail rotor. Findings – The results of the calculation demonstrate the feasibility of the established method for analyzing ducted tail rotor aerodynamic characteristics. Research limitations/implications – Although the global thrust and power of ducted tail‐rotor could be obtained using current method, the exact flow filed (such as shroud pressure field and the flow over fan blade) calculations still rely on the complex three‐dimensional CFD technique that should be studied in future. Practical implications – A very useful method for the preliminary design of the ducted tail rotor. Originality/value – By comparing the calculated results with those of relevant experiment, it is proved that the method developed here is suitable for the calculations in the field of rotor aerodynamics.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Feb 1, 2005
Keywords: Aerodynamics; Rotary engines; Finite volume methods
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