Experimental investigations on the performance of a modified co-flow jet aerofoil

K Balaji; G Jims John Wessley  lowast

doi:10.17485/IJST/v13i19.85

Article

Experimental investigations on the performance of a modified co-flow jet aerofoil

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Indian Journal of Science and Technology

DOI: 10.17485/IJST/v13i19.85

Year: 2020, Volume: 13, Issue: 19, Pages: 1873-1881

Original Article

Experimental investigations on the performance of a modified co-flow jet aerofoil

K Balaji^1,2, G Jims John Wessley^3∗

1 Research Scholar, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore, 641114, Tamil Nadu, India
2 Assistant Professor, Department of Aeronautical Engineering, Sanjay Ghodawat University, Kolhapur, 416118, Maharashtra, India. Tel.: +91-9790115696
3 Assistant Professor, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore, 641 114, Tamil Nadu, India. Tel.: +91-9487846906

∗Corresponding author:
G Jims John Wessley
Assistant Professor, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore, 641 114, Tamil Nadu, India.
Tel: +91-9487846906
Email: [email protected]

Received Date:01 April 2020, Accepted Date:22 May 2020, Published Date:18 June 2020

This work is licensed under a Creative Commons Attribution 4.0 International License.

Abstract

Objectives: To study the performance of a Modified Co Flow Jet (MCFJ) aerofoil with a converging nozzle located at the leading edge so as to reduce the pumping power. Methods: The experimental investigations are conducted on a base aerofoil and a modified CFJ (MCFJ) aerofoil in a subsonic tunnel at various angle of attack (AOA). The output performance parameters like coefficient of Lift (CL), Coefficient of drag (CD) and Lift are obtained for both the aerofoil and the results are compared. Findings: The result shows that the stalling angle of the MCFJ aerofoil advanced by 5◦ providing better flow characteristics than the baseline aerofoil. The lift increases up to 43% during the critical angle of attack of 25◦ in the MCFJ aerofoil. Novelty: In the present study, a convergent nozzle is placed near the leading edge of the CFJ aerofoil which effectively controls the mass flow rate of the flow during all phases of flight, thereby resulting in improved aerodynamic performance. Applications: This novel concept can be used for improved aerodynamic performance of MCFJ aerofoil with reduced pumping power. Also, it is possible to obtain improved performance of CFJ Method at all phases of flight by controlling the flow velocity by using the convergent nozzle.

Keywords: Modified co-flow jet; Angle of attack; Coefficient of lift; Coefficient of lift and drag; Aerodynamic performance

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Copyright

© 2020 Balaji, Wessley. This is an open access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.
Published By Indian Society for Education and Environment (iSee)