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Influence of active cowl deflection during buzz cycle of an axisymmetric supersonic intake

Published online by Cambridge University Press:  28 April 2025

S. Rao ,
P. Kumar Open the ORCID record for P. Kumar [Opens in a new window] ,
L. Srinivasa Rao Open the ORCID record for L. Srinivasa Rao [Opens in a new window]  and
S. Das Open the ORCID record for S. Das [Opens in a new window]
S. Rao
Affiliation:
Department of Space Engineering and Rocketry, Birla Institute of Technology, Mesra, Ranchi, India
P. Kumar
Affiliation:
Department of Space Engineering and Rocketry, Birla Institute of Technology, Mesra, Ranchi, India
L. Srinivasa Rao
Affiliation:
Department of Space Engineering and Rocketry, Birla Institute of Technology, Mesra, Ranchi, India
S. Das*
Affiliation:
Department of Space Engineering and Rocketry, Birla Institute of Technology, Mesra, Ranchi, India
*
Corresponding author: Sudip Das; Email: [email protected]
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Abstract

Supersonic intakes, under adverse operating conditions, can have unwanted oscillations of shock system internal and external to its duct, known as intake buzz. These buzz instabilities degrade intake performance by causing violent pressure fluctuations, reducing mass flow, decreasing thrust, and leading to combustion instabilities as well. This study examines the onset of this buzz in an axisymmetric intake with various throttles and investigates the effects of dynamic angular deflection of a portion of the cowl on the resulting buzz phenomena. Computations and experiments were conducted at Mach number of 2.0 to obtain the buzz in an axisymmetric intake and investigate its behaviour under various throttle conditions. Dailey-type buzz is observed to be predominant for the present axisymmetric intake, and it has been also quantified that the time period of oscillations for higher throttling ratios is not constant. A technique of dynamically varying the portion of the cowl tip about a pivot point was attempted here to eliminate the intake buzz during onset as well as during a complete buzz cycle. It has been found that the current technique is useful in seizing the buzz shock expulsion from the intake duct, hence restricting unstart and further adversities.

Keywords

buzzthrottlesupersonic intakeaxisymmetric intakesdynamic deflection
Type
Research Article
Information
The Aeronautical Journal , First View , pp. 1 - 23
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Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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