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112323

Investigation of Air Flow over Delta and Cranked Arrow Delta Wings.

Article

Last updated: 22 Jan 2023

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Subjects

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Tags

Mechanical Power Engineering

Abstract

Delta wing shapes are unique in their structure advantages and aerodynamic characteristics. On supersonic designing, a delta wing shape is often used to reduce drag and achieve the optimal performance. In this study, a commercial software (ANSYS 15) is used to investigate the performance of two delta wing shapes (simple delta wing and cranked arrow delta wing) at different angles of attack (5° to 65°) and different flow speeds (M = 0.15 to 1.4) in order to obtain the lift and drag coefficients, pressure distribution around the investigated wings, and velocity filed. The results indicate that: (i) at subsonic speed (M = 0.15 to 0.8), the lift coefficient for the cranked arrow delta wing increases by about 25%. While the drag coefficient in case of cranked arrow delta wing increases by a value reaches 5%, as the area of the cranked arrow delta wing is less by about 7%, this leads to decreasing drag force for the cranked arrow wing, which improves its performance. The lift and drag coefficients increase with increasing Mach number, the rate of increase is higher in the cranked arrow delta wing. In cranked arrow delta wing, vortex breakdown is delayed than that in simple delta wing, which makes the cranked arrow more stable. In addition, the cut parts from cranked arrow at trailing edge help to avoid the effect of vortex breakdown on the wing. (ii) At supersonic speed (M = 1.2 to M = 1.4), the lift coefficient of the cranked arrow delta wing is higher than that for simple delta wing by about 15%, while the increase in the drag coefficient does not exceed 2%, which increases cranked arrow wing's performance. The lift and drag coefficients decrease with increasing Mach number, the rate of decrease is higher in the cranked arrow delta wing. In the cranked arrow delta wing as Mach number increases, a better pressure distribution over the wing surface is observed which improves the stability during flight and maneuvering.

DOI

10.21608/bfemu.2020.112323

Keywords

Delta Wing, Cranked Arrow Delta Wing, angle of attack, Span, Chord, Lift Coefficient, Drag Coefficient, Vortex Breakdown

Authors

First Name

Ahmed

Last Name

Draz

MiddleName

Mohamed Mohamed

Affiliation

A mechanical power engineer , Researcher at Mechanical Power Engineering Department. Faculty of Engineering, Mansoura University

Email

eahmeddraz@gmail.com

City

-

Orcid

-

First Name

H.

Last Name

El Saadany

MiddleName

M.

Affiliation

Professor at Mechanical Power Engineering Department. Faculty of Engineering, Mansoura University

Email

hmsaadny@yahoo.com

City

-

Orcid

-

First Name

M.

Last Name

Awad

MiddleName

M.

Affiliation

Associate Professor at Mechanical Power Engineering Department, Faculty of Engineering, Mansoura University

Email

m_m_awad@mans.edu.eg.com

City

-

Orcid

-

First Name

W.

Last Name

El Awady

MiddleName

M.

Affiliation

Assistant Professor at Mechanical Power Engineering Department, Faculty of Engineering, Mansoura University

Email

welawady@mans.edu.eg

City

-

Orcid

-

Volume

45

Article Issue

2

Related Issue

14075

Issue Date

2020-06-01

Receive Date

2019-11-19

Publish Date

2020-09-13

Page Start

1

Page End

9

Print ISSN

1110-0923

Online ISSN

2735-4202

Article File

BFEMU_Volume 45_Issue 2_Pages 1-9.pdf

PDF . 1.3MB

Link

https://bfemu.journals.ekb.eg/article_112323.html

Detail API

https://bfemu.journals.ekb.eg/service?article_code=112323

Order

7

Type

Research Studies

Type Code

1,205

Publication Type

Journal

Publication Title

MEJ. Mansoura Engineering Journal

Publication Link

https://bfemu.journals.ekb.eg/

MainTitle

-

Details

Type

Article

Created At

22 Jan 2023