Thrust generation caused by flapping airfoils in a biplane configuration

Date

2003-05-01

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

163
views

0
downloads

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% more thrust than a single flapping airfoil. Turbulence in the flow further augments the thrust generation. For a maximum thrust at a given flapping frequency, an optimization of the flapping motion parameters is needed.

URI

https://hdl.handle.net/11511/30868

Journal

JOURNAL OF AIRCRAFT

DOI

https://doi.org/10.2514/2.3124

Collections

Graduate School of Natural and Applied Sciences, Article

Suggestions

OpenMETU
Core

Parallel computation of flows around flapping airfoils in biplane configuration Tuncer, İsmail Hakkı; Kaya, Muhammed Çağrı (2002-05-22) 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.
AERODYNAMIC ANALYSIS OF SUPERSONIC FLOW OVER A SIMPLE AIRCRAFT GEOMETRY BY USING CST AND PANEL METHODS Uğur, Levent; Turan, Sena; Gedik, Ramazan Kürşat; Adam, Ali Ata; Sezer Uzol, Nilay; Ertem, Sercan; Ayan, Erdem (2021-09-10) In this paper, the aerodynamic properties of a selected aircraft geometry are calculated in supersonic flow condition using PANAIR. PANAIR is an open-source high-order panel method solver for irrotational and inviscid flows and it is more efficient than higher fidelity CFD analyses for the preliminary design process since it is faster and easier to use. A batch of supersonic analyses is completed for different wing/body configurations for the selected aircraft geometry and with various panel g...
Aerodynamic optimization of turbomachinery cascades using Euler/boundary-layer coupled genetic algorithms Oksuz, O; Akmandor, IS; Kavsaoglu, MS (American Institute of Aeronautics and Astronautics (AIAA), 2002-05-01) A new methodology is developed to find the optimal aerodynamic performance of a turbine cascade. A boundary-layer coupled Euler algorithm and a genetic algorithm are linked within an automated optimization loop. The multiparameter objective function is based on the blade loading. For a given inlet Mach number and baseline cascade geometry, the flow inlet and exit angles, the blade thickness and the solidity are optimized by a robust genetic algorithm. First, the Sanz subcritical turbine cascade is selected ...
Aerodynamic optimization of horizontal axis wind turbine blades by using CST method, BEM theory and genetic algorithm Oğuz, Keriman; Sezer Uzol, Nilay; Department of Aerospace Engineering (2019) In this thesis, an aerodynamic design and optimization study for rotor airfoils and blades of Horizontal Axis Wind Turbines (HAWTs) is performed by using different airfoil representations and genetic algorithm. Two airfoil representations, the Class-Shape Transformation (CST) method and the Parametric Section (PARSEC) method, are used for the airfoil geometry designs. Their aerodynamic data is obtained by a potential flow solver software, XFOIL. The Blade Element Momentum (BEM) theory is used to calculate t...
Thrust generation due to airfoil flapping Tuncer, İsmail Hakkı (American Institute of Aeronautics and Astronautics (AIAA), 1996-02-01) Thrust generation on a single flapping airfoil and a flapping/stationary airfoil combination in tandem is studied parametrically. A multiblock Navier-Stokes solver is employed to compute unsteady flowfields. The unsteady flow-field around a single flapping airfoil is also computed by an unsteady potential how code, The numerical solutions predict thrust generation in flapping airfoils and a significant augmentation of thrust in flapping/stationary airfoil combinations in tandem. The propulsive efficiency is...

Citation Formats

İ. H. Tuncer and M. Ç. Kaya, “Thrust generation caused by flapping airfoils in a biplane configuration,” JOURNAL OF AIRCRAFT, pp. 509–515, 2003, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/30868.