Computational Study of Flow around a NACA 0012 Wing Flapped at Different Flap Angles with Varying Mach Numbers

Tousif Ahmed; Md. Amin; S.M. Islam; Shabbir Ahmed

Computational Study of Flow Around a NACA 0012 Wing Flapped at Different Flap Angles with Varying Mach Numbers

Tousif Ahmed * §

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Md. Tanjin Amin §

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S.M. Rafiul Islam §

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Shabbir Ahmed §

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§ Department of Mechanical Engineering, Bangladesh Uni...

Computational Study of Flow Around a NACA 0012 Wing Flapped at Different Flap Angles with Varying Mach Numbers

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Abstract

The analysis of two dimensional (2 D) flow over NACA 0012 airfoil is validated with NASA Langley Research Center validation cases. The k-ω shear stress transport (SST) model is utilized to predict the flow accurately along with turbulence intensities 1% and 5% at velocity inlet and pressure outlet respectively. The computational domain is composed of 120000 structured cells. In order to enclose the boundary layer method the enhancement of the grid near the airfoil is taken care off. This validated simulation technique is further used to analyse aerodynamic characteristics of plain flapped NACA 0012 airfoil subjected to different flap angles and Mach number. The calculation of lift coefficients (CL), drag coefficients (CD) and CL/CD ratio at different operating conditions show that with increasing Mach number (M) CL increases but CD remains somewhat constant. Moreover, a rapid drastic decrease is observed for CL and an abrupt upsurge is observed for Cd with velocity approaching to the sonic velocity. In all cases range and endurance are decreased, as both values of CL/CD and √CL/CD are declined.

References

11 Cites in Article

Reference Format

1. 2D NACA 0012 Airfoil Validation Cases.
2. Douvi Eleni,I. Tsavalos,Margaris Athanasios,Dionissios (2012). Evaluation of the turbulence models for the simulation of the flow over a National Advisory Committee for Aeronautics (NACA) 0012 airfoil. Journal of Mechanical Engineering Research, 4(3), 100-111.
3. Information on k-ω SST model.
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CrossRef DOI
10. N. Gregory,C. O'Reilly (1970). Low-Speed Aerodynamic Characteristics of NACA 0012 Aerofoil Sections, including the Effects of Upper-Surface Roughness Simulation Hoar Frost. NASA R&M
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Funding

No external funding was declared for this work.

Conflict of Interest

The authors declare no conflict of interest.

Ethical Approval

No ethics committee approval was required for this article type.

Data Availability

Not applicable for this article.

How to Cite This Article

Tousif Ahmed, Md. Tanjin Amin, S.M. Rafiul Islam, Shabbir Ahmed. 2014. "Computational Study of Flow Around a NACA 0012 Wing Flapped at Different Flap Angles with Varying Mach Numbers". Global Journal of Research in Engineering - J: General Engineering GJRE-J Volume 13 (GJRE Volume 13 Issue 51 (J4)).

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GJRE Volume 13 Issue 51 (J4)

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Journal Specifications

Crossref Journal DOI 10.17406/gjre

Print ISSN 0975-5861

e-ISSN 2249-4596

Keywords

drag coefficient (CD)drag polar endurance (E)flap angle (δ)k-ω shear stress transport (SST) model lift coefficient (CL)lift curve mach number (M)NACA 0012 airfoil range (R)

Classification

GJRE-J Classification FOR Code: 091399

Submission ReceivedDecember 16, 2012
Peer Review Double Blind
Handling Editor
Accepted January 5, 2013
Published December 2, 2013

Version of record

v1.2

Issue date

December 2, 2013

Language

English

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Article Matrices

Total Score: 104

Country: Bangladesh

Subject: Global Journal of Research in Engineering - J: General Engineering

Authors: Tousif Ahmed, Md. Tanjin Amin, S. M. Rafiul Islam, Shabbir Ahmed (PhD/Dr. count: 0)

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