Numerical analysis of supersonic co-flow jet with varying lip thickness

Abstract

Purpose

This study aims to present the numerical study on supersonic jet mixing characteristics of the co-flow jet by varying lip thickness (LT). The LT chosen for the study is 2 mm, 7.75 mm and 15 mm.

Design/methodology/approach

The primary nozzle is designed for delivering Mach 2.0 jet, whereas the secondary nozzle is designed for delivering Mach 1.6 jet. The Nozzle pressure ratio chosen for the study is 3 and 5. To study the mixing characteristics of the co-flow jet, total pressure and Mach number measurements were taken along and normal to the jet axis. To validate the numerical results, the numerical total pressure values were also compared with the experimental result and it is proven to have a good agreement.

Findings

The results exhibit that, the 2 mm lip is shear dominant. The 7.75 mm and 15 mm lip is wake dominant. The jet interaction along the jet axis was also studied using the contours of total pressure, Mach number, turbulent kinetic energy and density gradient. The radial Mach number contours at the various axial location of the jet was also studied.

Practical implications

The effect of varying LT in exhaust nozzle plays a vital role in supersonic turbofan aircraft.

Originality/value

Supersonic co-flowing jet mixing effectiveness by varying the LT between the primary supersonic nozzle and the secondary supersonic nozzle has not been analyzed in the past.

Citation

K, S.K., R, N.S., K, A. and B.R., S.K. (2022), "Numerical analysis of supersonic co-flow jet with varying lip thickness", Aircraft Engineering and Aerospace Technology, Vol. 94 No. 2, pp. 198-209. https://doi.org/10.1108/AEAT-05-2021-0143