Experimental Validation on Lift Increment of a Flapping Rotary Wing with Boring-hole Design

Chen Long; Yan Wanfang; Wu Jianghao

doi:10.1016/j.proeng.2014.12.706

Experimental Validation on Lift Increment of a Flapping Rotary Wing with Boring-hole Design

Chen Long
, Yan Wanfang
, Wu Jianghao^*

^*Corresponding author for this work

School of Transportation Science and Engineering

Beihang University

Research output: Contribution to journal › Conference article › peer-review

11 Scopus citations

Abstract

The flapping rotary wing as a novel layout of micro air vehicle (MAV) remains being tested. Boring-hole design was applied to decrease the negative lift generated in wing's upstroke motion. The lift of traditional and boring-hole wingwere measured, contrasted and analyzed by experiments. Another series of experiments was conducted to explore the effect of the hinge material. It is indicated that a critical angle of attack (α_t) exist to confirm the lift increment of the perforated wing, and the maximum increment can be up to 35% of the maximummean lift.

Original language	English
Pages (from-to)	1543-1547
Number of pages	5
Journal	Procedia Engineering
Volume	99
DOIs	https://doi.org/10.1016/j.proeng.2014.12.706
State	Published - 2015
Event	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2014 - Shanghai, China Duration: 24 Sep 2014 → 26 Sep 2014

Keywords

boring-hole design
experimental validation
flapping rotary wing
lift increment

Access to Document

10.1016/j.proeng.2014.12.706

Cite this

@article{dcae2d86ef744cdd9c7209bbc57b6dab,

title = "Experimental Validation on Lift Increment of a Flapping Rotary Wing with Boring-hole Design",

abstract = "The flapping rotary wing as a novel layout of micro air vehicle (MAV) remains being tested. Boring-hole design was applied to decrease the negative lift generated in wing's upstroke motion. The lift of traditional and boring-hole wingwere measured, contrasted and analyzed by experiments. Another series of experiments was conducted to explore the effect of the hinge material. It is indicated that a critical angle of attack (αt) exist to confirm the lift increment of the perforated wing, and the maximum increment can be up to 35\% of the maximummean lift.",

keywords = "boring-hole design, experimental validation, flapping rotary wing, lift increment",

author = "Chen Long and Yan Wanfang and Wu Jianghao",

note = "Publisher Copyright: {\textcopyright} 2015 The Authors.; Asia-Pacific International Symposium on Aerospace Technology, APISAT 2014 ; Conference date: 24-09-2014 Through 26-09-2014",

year = "2015",

doi = "10.1016/j.proeng.2014.12.706",

language = "英语",

volume = "99",

pages = "1543--1547",

journal = "Procedia Engineering",

issn = "1877-7058",

publisher = "Elsevier Ltd",

}

TY - JOUR

T1 - Experimental Validation on Lift Increment of a Flapping Rotary Wing with Boring-hole Design

AU - Long, Chen

AU - Wanfang, Yan

AU - Jianghao, Wu

PY - 2015

Y1 - 2015

N2 - The flapping rotary wing as a novel layout of micro air vehicle (MAV) remains being tested. Boring-hole design was applied to decrease the negative lift generated in wing's upstroke motion. The lift of traditional and boring-hole wingwere measured, contrasted and analyzed by experiments. Another series of experiments was conducted to explore the effect of the hinge material. It is indicated that a critical angle of attack (αt) exist to confirm the lift increment of the perforated wing, and the maximum increment can be up to 35% of the maximummean lift.

AB - The flapping rotary wing as a novel layout of micro air vehicle (MAV) remains being tested. Boring-hole design was applied to decrease the negative lift generated in wing's upstroke motion. The lift of traditional and boring-hole wingwere measured, contrasted and analyzed by experiments. Another series of experiments was conducted to explore the effect of the hinge material. It is indicated that a critical angle of attack (αt) exist to confirm the lift increment of the perforated wing, and the maximum increment can be up to 35% of the maximummean lift.

KW - boring-hole design

KW - experimental validation

KW - flapping rotary wing

KW - lift increment

UR - https://www.scopus.com/pages/publications/84978086875

U2 - 10.1016/j.proeng.2014.12.706

DO - 10.1016/j.proeng.2014.12.706

M3 - 会议文章

AN - SCOPUS:84978086875

SN - 1877-7058

VL - 99

SP - 1543

EP - 1547

JO - Procedia Engineering

JF - Procedia Engineering

T2 - Asia-Pacific International Symposium on Aerospace Technology, APISAT 2014

Y2 - 24 September 2014 through 26 September 2014

ER -

Experimental Validation on Lift Increment of a Flapping Rotary Wing with Boring-hole Design

Abstract

Keywords

Access to Document

Other files and links

Fingerprint

Cite this