Paper Title:
Unsteady Compressible Flow over Heaving Bodies Using an Implicit RANS Solver

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.

Chapter 22: Metrology and Measurement
Edited by
Wu Fan
K. S. Kumar, S. V. Sajjan, "Unsteady Compressible Flow over Heaving Bodies Using an Implicit RANS Solver", Applied Mechanics and Materials, Vols. 110-116, pp. 4589-4597, Oct. 2011
Online since
October 2011
US$ 32,-
Authors: K. Siva Kumar, Sharanappa V. Sajjan
Chapter 17: Precision Molding Processes
Abstract:Unsteady Reynolds-averaged Navier-Stokes (RANS) computations are presented for low Mach number flow past a combined pitching and plunging...
Authors: Ahmad Kamran, Zhi Gang Wu, Muhammad Amjad Sohail
Chapter 2: Applied Mechanics and Mechanical Engineering
Abstract:This research paper presents the CFD analysis of oscillating airfoil during pitch cycle. Unsteady subsonic flow is simulated for pitching...
Authors: Yu Qian, Jun Li Yang, Xiao Jun Xiang, Ming Qiang Chen
Chapter 3: General Mechanical Engineering
Abstract:The unsteady aerodynamic loads are the basic of the aeroelasitc. This paper focuses on the computation of the unsteady aerodynamic loads for...
Authors: Saif Akram, Nadeem Hasan, Aqib Khan
Chapter 2: Fluid Dynamics, CFD and other Computational Methods
Abstract:A numerical investigation of two-dimensional unsteady, viscous and laminar compressible flow past an asymmetric biconvex circular-arc...
Authors: Xiang Shen, Theodosios Korakianitis, Eldad Avital
Chapter 8: Researching and Designing in Aerospace Engineering
Abstract:The prescribed surface curvature distribution blade design (CIRCLE) method optimises aerofoils and blades by controlling curvature continuity...