Zobrazeno 1 - 6
of 6
pro vyhledávání: '"Nandita Yeshala"'
Autor:
Brian E. Wake, Claude G. Matalanis, Lakshmi N. Sankar, Nandita Yeshala, Daniel Opoku, Byung-Young Min
This work presents progress on a detailed aerodynamic evaluation of Miniature Trailing-Edge Effectors (MiTEs) for active rotor control. We begin with a 2D computational fluid dynamics (CFD) study focused on establishing the dependency of MiTE effecti
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::ecda1713f96359b17c9416e33e760be2
Publikováno v:
50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.
Multi-scale modeling of synthetic jet devices is em ployed to investigate the effect of active flow control (AFC) on fuselage drag reduction. The flow field in the vicinity of the synthetic jet devices was modeled using a Lattice Boltzmann equation (
Autor:
Nandita Yeshala, Lakshmi N. Sankar
Publikováno v:
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.
A coupled Lattice Boltzmann – Navier-Stokes methodology in three dimensions is implemented for modeling flow control phenomena. A one cell overlap between the Lattice Boltzmann (LB) and Navier-Stokes (NS) grids is used to exchange information betwe
Autor:
Nandita Yeshala, Lakshmi N. Sankar
Publikováno v:
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.
A coupled Lattice Boltzmann – Navier-Stokes methodology is implemented for modeling flow control phenomena. The details of the implementation are presented in this paper. A one cell overlap between the Lattice Boltzmann (LB) and Navier-Stokes (NS)
Publikováno v:
4th Flow Control Conference.
Active flow control (AFC) has gained a great deal of attention in recent flow control research and applications. Use of AFC has shown improvement in aircraft performance by reduction in drag and increase in lift. The objective of the present study is
Publikováno v:
24th AIAA Applied Aerodynamics Conference.
The accuracy of the calculation of the tip vortex magnitude and the trajectory is very important in rotor calculations, especially in hover where it is the source of the induced velocity that in turn affects the aerodynamic loads. Lower order schemes