Parallel computation of flows around flapping airfoils in biplane configuration

Date

2002-05-22

Author

Tuncer, İsmail Hakkı
Kaya, Muhammed Çağrı

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

188
views

0
downloads

Unsteady, laminar flows over flapping airfoils in biplane configuration are computed on overset grids. The overset grid solutions are obtained in parallel in a cluster environment. It is shown that airfoils in biplane configuration and oscillating in pitch and plunge with a proper phase shift between them enhance the thrust production significantly.

Subject Keywords

Affordable computing, Distributed computing, Euler and Navier Stokes solvers, Unsteady flows, Domain decomposition

URI

https://hdl.handle.net/11511/30808

DOI

https://doi.org/10.1016/b978-044450680-1/50066-8

Collections

Graduate School of Natural and Applied Sciences, Conference / Seminar

Suggestions

OpenMETU
Core

Parallel optimization of flapping airfoils in a biplane configuration for maximum thrust Tuncer, İsmail Hakkı (2004-05-27) Flapping airfoils in a biplane configuration are optimized for a maximum thrust production. A parallel Navier-Stokes solver on overset grids and a gradient based parallel optimization method are employed. The periodic flapping motion of airfoils in a plane configuration is described in a combined pitch and plunge. The pitch and plunge amplitudes and the phase shift between them are optimized for a range of flapping frequencies. It is shown that at low flapping frequencies, flapping airfoils in a biplane con...
Experimental analysis of flow structure on moderate sweep delta wing Öztürk, İlhan; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2014) Experimental investigation of flow over a 45° moderate swept delta wing is performed using laser illuminated smoke visualization, surface pressure measurements, and Laser Doppler Anemometry (LDA) techniques in low-speed wind tunnel. The formation of leading-edge vortices and their breakdown, and three-dimensional separation from the surface of the wing are studied at broad range of attack angles and Reynolds numbers. Smoke visualizations are performed at three different cross flow planes along with vortex a...
Experimental Investigation of the Effects of Winglets on the Tip Vortex Behavior of a Model Horizontal Axis Wind Turbine Using Particle Image Velocimetry Ostovan, Yasar; Akpolat, M. Tugrul; Uzol, Oğuz (2019-02-01) This study presents an experimental investigation on the effects of winglets on the near wake flow around the tip region and on the tip vortex characteristics downstream of a 0.94 m diameter three-bladed horizontal axis wind turbine (HAWT) rotor. Phase-locked 2D particle image velocimetry (PIV) measurements are performed with and without winglets covering 120 deg of azimuthal progression of the rotor. The impact of using winglets on the flow field near the wake boundary as well as on the tip vortex characte...
Experimental investigation of the effects of tip-injection on the aerodynamic loads and wake characteristics of a model horizontal axis wind turbine rotor Abdulrahim, Anas; Uzol, Oğuz; Department of Aerospace Engineering (2014) In this study, tip injection is implemented on a model Horizontal Axis Wind Turbine (HAWT) rotor to investigate the power and thrust coefficient variations as well as the wake characteristics. The model wind turbine has a 0.95 m diameter 3-bladed rotor with non-linearly twisted and tapered blades that has NREL S826 profile. The nacelle, hub and the blades are specifically designed to allow pressurized air to pass through and get injected from the tips while the rotor is rotating. The experiments are perform...
Thrust generation caused by flapping airfoils in a biplane configuration Tuncer, İsmail Hakkı; Kaya, Muhammed Çağrı (2003-05-01) Unsteady, viscous flows over flapping airfoils in a biplane configuration are computed on moving overset grids. The overset grid solutions are obtained in parallel in a distributed memory environment. Unsteady flowfields are described by particle traces: Time-averaged thrust values are obtained from the integration of the unsteady drag coefficient. It is shown that airfoils in a biplane configuration and oscillating in a combined pitch and plunge motion with a proper phase shift between them produce 20-40% ...

Citation Formats

İ. H. Tuncer and M. Ç. Kaya, “Parallel computation of flows around flapping airfoils in biplane configuration,” 2002, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/30808.