Please use this identifier to cite or link to this item: http://scholarbank.nus.edu.sg/handle/10635/116703
Title: Computation of the flows over flapping airfoil by the euler equations
Authors: Yang, S.
Luo, S.
Liu, F.
Tsai, H.-M. 
Issue Date: 2005
Source: Yang, S.,Luo, S.,Liu, F.,Tsai, H.-M. (2005). Computation of the flows over flapping airfoil by the euler equations. 43rd AIAA Aerospace Sciences Meeting and Exhibit - Meeting Papers : 1133-1155. ScholarBank@NUS Repository.
Abstract: To investigate the mechanism of thrust generation by Happing airfoils, the inviscid version of a three-dimensional unsteady compressible Euler/Navier Stokes flow solver is used to simulate the flow field around flapping airfoil NACA 0012 in an uniform stream of low speeds. Sinusoidally plunging or/and pitching oscillations are studied. The compressible Euler code with a low free-stream Mach number of 0.1 or 0.05 can simulate the incompressible flows without leading-edge separation. The wake-flow structures are visualized by the numerical methods: vorticity filled-contours, perturbation-velocity vector plots, and streamlines of the velocity field relative to the flapping airfoil. The computed wake-vortex structures and the time-averaged thrust coefficients, input-power coefficients, and the efficiency over a period of the oscillation versus the Strouhal number based on the total excursion of the trailing edge of the airfoil for a number of plunging and pitching cases agree well with the test data and the non-linear incompressible potential-flow solutions in the literature. The agreement with the test data decreases when leading-edge vortices appear and become strong enough to interfere with the trailing-edge vortices.
Source Title: 43rd AIAA Aerospace Sciences Meeting and Exhibit - Meeting Papers
URI: http://scholarbank.nus.edu.sg/handle/10635/116703
Appears in Collections:Staff Publications

Show full item record
Files in This Item:
There are no files associated with this item.

Page view(s)

23
checked on Feb 18, 2018

Google ScholarTM

Check


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.