A computational study on effect of pitch difference in pure plunging tandem wings

Research output: Contribution to journalArticle

Abstract

Flapping wing in tandem configuration may offer enhanced aerodynamic performance at low Reynolds number, in which micro air vehicles operate. The present study aims to investigate the effect of fore-hind wing pitch difference on the aerodynamic performance of tandem wings. To that end, two-dimensional, laminar flow around two thin flat airfoils that are sinusoidally plunging in phase with each other, were computationally simulated at a Reynolds number of 10000, using a flow solver in an Arbitrary Lagrangian-Eulerian framework. The fore wing pitch angle was fixed to 10°, while the hind wing pitch angle was varied between -10°, 0°, 10° and 20°. Numerical results shows that aerodynamic performance of the fore wing may be affected by the hind wing pitch angle and that tandem wings may offer improved lift to drag efficiency at some optimal fore-hind wing pitch difference compared to twice the results of a similar single wing case. In addition, the complex fore-hind wing vortex interaction is also affected by the hind wing pitch angle.

Original languageEnglish
Article number012004
JournalIOP Conference Series: Materials Science and Engineering
Volume152
Issue number1
DOIs
Publication statusPublished - 31 Oct 2016

Fingerprint

Aerodynamics
Reynolds number
Micro air vehicle (MAV)
Laminar flow
Airfoils
Drag
Vortex flow

ASJC Scopus subject areas

  • Materials Science(all)
  • Engineering(all)

Cite this

@article{a19c152086dd432db897e79b3f09147e,
title = "A computational study on effect of pitch difference in pure plunging tandem wings",
abstract = "Flapping wing in tandem configuration may offer enhanced aerodynamic performance at low Reynolds number, in which micro air vehicles operate. The present study aims to investigate the effect of fore-hind wing pitch difference on the aerodynamic performance of tandem wings. To that end, two-dimensional, laminar flow around two thin flat airfoils that are sinusoidally plunging in phase with each other, were computationally simulated at a Reynolds number of 10000, using a flow solver in an Arbitrary Lagrangian-Eulerian framework. The fore wing pitch angle was fixed to 10°, while the hind wing pitch angle was varied between -10°, 0°, 10° and 20°. Numerical results shows that aerodynamic performance of the fore wing may be affected by the hind wing pitch angle and that tandem wings may offer improved lift to drag efficiency at some optimal fore-hind wing pitch difference compared to twice the results of a similar single wing case. In addition, the complex fore-hind wing vortex interaction is also affected by the hind wing pitch angle.",
author = "{Mohammad Rasani}, {Mohammad Rasidi} and Nuawi, {Mohd. Zaki} and {Wan Mahmood}, {Wan Mohd Faizal} and Zambri Harun",
year = "2016",
month = "10",
day = "31",
doi = "10.1088/1757-899X/152/1/012004",
language = "English",
volume = "152",
journal = "IOP Conference Series: Materials Science and Engineering",
issn = "1757-8981",
publisher = "IOP Publishing Ltd.",
number = "1",

}

TY - JOUR

T1 - A computational study on effect of pitch difference in pure plunging tandem wings

AU - Mohammad Rasani, Mohammad Rasidi

AU - Nuawi, Mohd. Zaki

AU - Wan Mahmood, Wan Mohd Faizal

AU - Harun, Zambri

PY - 2016/10/31

Y1 - 2016/10/31

N2 - Flapping wing in tandem configuration may offer enhanced aerodynamic performance at low Reynolds number, in which micro air vehicles operate. The present study aims to investigate the effect of fore-hind wing pitch difference on the aerodynamic performance of tandem wings. To that end, two-dimensional, laminar flow around two thin flat airfoils that are sinusoidally plunging in phase with each other, were computationally simulated at a Reynolds number of 10000, using a flow solver in an Arbitrary Lagrangian-Eulerian framework. The fore wing pitch angle was fixed to 10°, while the hind wing pitch angle was varied between -10°, 0°, 10° and 20°. Numerical results shows that aerodynamic performance of the fore wing may be affected by the hind wing pitch angle and that tandem wings may offer improved lift to drag efficiency at some optimal fore-hind wing pitch difference compared to twice the results of a similar single wing case. In addition, the complex fore-hind wing vortex interaction is also affected by the hind wing pitch angle.

AB - Flapping wing in tandem configuration may offer enhanced aerodynamic performance at low Reynolds number, in which micro air vehicles operate. The present study aims to investigate the effect of fore-hind wing pitch difference on the aerodynamic performance of tandem wings. To that end, two-dimensional, laminar flow around two thin flat airfoils that are sinusoidally plunging in phase with each other, were computationally simulated at a Reynolds number of 10000, using a flow solver in an Arbitrary Lagrangian-Eulerian framework. The fore wing pitch angle was fixed to 10°, while the hind wing pitch angle was varied between -10°, 0°, 10° and 20°. Numerical results shows that aerodynamic performance of the fore wing may be affected by the hind wing pitch angle and that tandem wings may offer improved lift to drag efficiency at some optimal fore-hind wing pitch difference compared to twice the results of a similar single wing case. In addition, the complex fore-hind wing vortex interaction is also affected by the hind wing pitch angle.

UR - http://www.scopus.com/inward/record.url?scp=84998533012&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84998533012&partnerID=8YFLogxK

U2 - 10.1088/1757-899X/152/1/012004

DO - 10.1088/1757-899X/152/1/012004

M3 - Article

VL - 152

JO - IOP Conference Series: Materials Science and Engineering

JF - IOP Conference Series: Materials Science and Engineering

SN - 1757-8981

IS - 1

M1 - 012004

ER -