Unsteady Compressible Flow over Heaving Bodies Using an Implicit RANS Solver

Kumar, K. Siva; Sajjan, Sharanappa V.

Paper Titles

Combustion Properties of Norwegian Biomass: Wood Chips and Forest Residues, p.4564
A Cost-Effective Hardware Approach for Measuring Power Consumption of Modern Multi-Core Processors, p.4569
Effect of Steam Injection in Gas Turbine Combustion Chamber on the Performance of a Natural Gas Fired Combined Cycle Power Generation Unit, p.4574
Investigation of Nonlinear Acoustic Effects in Two-Dimensional Open Cavity Flow, p.4578
Unsteady Compressible Flow over Heaving Bodies Using an Implicit RANS Solver, p.4589
Accurate Calculation of the Natural Frequencies of Reticulated and Solid Cylindrical Composite Shells, p.4598
Failure Analysis of Low Pressure Evaporator Tubes in a Typical Combined Cycle Power Plant, p.4607
Reynolds Study of the Flow Induced Noise, p.4615
The Tribological Study of a Quinazolin-4-Ones Derivative as Additive in Liquid Paraffin, p.4623

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Paper Title:

Unsteady Compressible Flow over Heaving Bodies Using an Implicit RANS Solver

Periodical	Applied Mechanics and Materials (Volumes 110 - 116)
Main Theme	Mechanical and Aerospace Engineering
Edited by	Wu Fan
Pages	4589-4597
DOI	10.4028/www.scientific.net/AMM.110-116.4589
Citation	K. Siva Kumar et al., 2011, Applied Mechanics and Materials, 110-116, 4589
Online since	October, 2011
Authors	K. Siva Kumar, Sharanappa V. Sajjan
Keywords	Dual Time Stepping, Implicit Method, Plunging Wing, RANS Solver, Unsteady Flow
Price	US$ 28,-

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Abstract

Unsteady Reynolds-Averaged Navier-Stokes computations are presented for the flow over a pure plunging aerofoil and a plunging wing. The implicit RANS solver used for obtaining time-accurate solution is based on implicit finite volume nodal point spatial discretization scheme with dual time stepping. Baldwin and Lomax turbulence model has been used for the turbulence closure. The results are obtained in the form of aerodynamic coefficients, thrust coefficient and propulsion efficiency for two different cases over the aerofoil and wing and are compared with available literature.