Non-planarity to improve subsonic performance of delta wing at low angle of attack

Y. Y. Zheng; N. A. Ahmed

Non-planarity to improve subsonic performance of delta wing at low angle of attack

Y. Y. Zheng
, N. A. Ahmed

University of New South Wales
National University of Defense Technology

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

14 Citations (Scopus)

Abstract

The potential of nonplanarity to improve the lift generation of delta wings at subsonic speeds and low angles of attack was assessed through an experimental study. The solution features surfaces which deflect from the basic delta to form an X-configuration, and was inspired by the promises of high lift generation using vortex trapping on high aspect-ratio wings. Both load balance readings and detailed static pressure measurements were employed to enable a discussion of the effects of nonplanarity. Relative to the basic delta wing, the X-configuration displays an increase in lift at low angles of attack with corresponding increase in drag. An overall improvement in performance is displayed when compared leading edge vortex flaps (LEVFs).

Original language	English
Title of host publication	43rd Fluid Dynamics Conference
Publication status	Published - 2013
Externally published	Yes
Event	43rd AIAA Fluid Dynamics Conference - San Diego, CA, United States Duration: 24 Jun 2013 → 27 Jun 2013

Publication series

Name	43rd Fluid Dynamics Conference

Conference

Conference	43rd AIAA Fluid Dynamics Conference
Country/Territory	United States
City	San Diego, CA
Period	24/06/13 → 27/06/13

ASJC Scopus subject areas

Fluid Flow and Transfer Processes
Energy Engineering and Power Technology
Aerospace Engineering
Mechanical Engineering

Cite this

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title = "Non-planarity to improve subsonic performance of delta wing at low angle of attack",

abstract = "The potential of nonplanarity to improve the lift generation of delta wings at subsonic speeds and low angles of attack was assessed through an experimental study. The solution features surfaces which deflect from the basic delta to form an X-configuration, and was inspired by the promises of high lift generation using vortex trapping on high aspect-ratio wings. Both load balance readings and detailed static pressure measurements were employed to enable a discussion of the effects of nonplanarity. Relative to the basic delta wing, the X-configuration displays an increase in lift at low angles of attack with corresponding increase in drag. An overall improvement in performance is displayed when compared leading edge vortex flaps (LEVFs).",

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year = "2013",

language = "English",

isbn = "9781624102141",

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AU - Zheng, Y. Y.

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N2 - The potential of nonplanarity to improve the lift generation of delta wings at subsonic speeds and low angles of attack was assessed through an experimental study. The solution features surfaces which deflect from the basic delta to form an X-configuration, and was inspired by the promises of high lift generation using vortex trapping on high aspect-ratio wings. Both load balance readings and detailed static pressure measurements were employed to enable a discussion of the effects of nonplanarity. Relative to the basic delta wing, the X-configuration displays an increase in lift at low angles of attack with corresponding increase in drag. An overall improvement in performance is displayed when compared leading edge vortex flaps (LEVFs).

AB - The potential of nonplanarity to improve the lift generation of delta wings at subsonic speeds and low angles of attack was assessed through an experimental study. The solution features surfaces which deflect from the basic delta to form an X-configuration, and was inspired by the promises of high lift generation using vortex trapping on high aspect-ratio wings. Both load balance readings and detailed static pressure measurements were employed to enable a discussion of the effects of nonplanarity. Relative to the basic delta wing, the X-configuration displays an increase in lift at low angles of attack with corresponding increase in drag. An overall improvement in performance is displayed when compared leading edge vortex flaps (LEVFs).

UR - https://www.scopus.com/pages/publications/84883501755

M3 - Conference contribution

AN - SCOPUS:84883501755

SN - 9781624102141

T3 - 43rd Fluid Dynamics Conference

BT - 43rd Fluid Dynamics Conference

T2 - 43rd AIAA Fluid Dynamics Conference

Y2 - 24 June 2013 through 27 June 2013

ER -

Non-planarity to improve subsonic performance of delta wing at low angle of attack

Abstract

Publication series

Conference

ASJC Scopus subject areas

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