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Control of shock-induced vortex breakdown on a delta-wing-body configuration in the transonic regime

Published online by Cambridge University Press:  26 November 2021

Rajan B. Kurade Open the ORCID record for Rajan B. Kurade [Opens in a new window] ,
L. Venkatakrishnan Open the ORCID record for L. Venkatakrishnan [Opens in a new window]  and
G. Jagadeesh Open the ORCID record for G. Jagadeesh [Opens in a new window]
Rajan B. Kurade*
Affiliation:
Principal Scientist, CSIR - National Aerospace Laboratories, Bangalore – 560017, India
L. Venkatakrishnan
Affiliation:
Chief Scientist, CSIR - National Aerospace Laboratories, Bangalore – 560017, India
G. Jagadeesh
Affiliation:
Professor, Department of Aerospace Engineering, Indian Institute of Science, Bangalore – 560012, India
*
E-mail: rajankurade@nal.res.in
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Abstract

Shock-induced vortex breakdown, which occurs on the delta wings at transonic speed, causes a sudden and significant change in the aerodynamic coefficients at a moderate angle-of-attack. Wind-tunnel tests show a sudden jump in the aerodynamic coefficients such as lift force, pitching moment and centre of pressure which affect the longitudinal stability and controllability of the vehicle. A pneumatic jet operated at sonic condition blown spanwise and along the vortex core over a 60° swept delta-wing-body configuration is found to be effective in postponing this phenomenon by energising the vortical structure, pushing the vortex breakdown location downstream. The study reports that a modest level of spanwise blowing enhances the lift by about 6 to 9% and lift-to-drag ratio by about 4 to 9%, depending on the free-stream transonic Mach number, and extends the usable angle-of-attack range by 2°. The blowing is found to reduce the magnitude of unsteady pressure fluctuations by 8% to 20% in the aft portion of the wing, depending upon the method of blowing. Detailed investigations carried out on the location of blowing reveal that the blowing close to the apex of the wing maximises the benefits.

Keywords

Vortex breakdownShock-induced vortex breakdownTransonic regimeDelta wingsFlow controlSpan-wise blowingAlong-the-core blowing
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1299 , May 2022 , pp. 768 - 792
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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