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Effect of microramps on flare-induced shock – boundary-layer interaction

Published online by Cambridge University Press:  06 November 2019

T. Nilavarasan Open the ORCID record for T. Nilavarasan [Opens in a new window] ,
G. N. Joshi  and
A. Misra
T. Nilavarasan*
Affiliation:
Department of Aerospace Engineering, Defence Institute of Advanced Technology, Pune, 411025, Maharashtra, India
G. N. Joshi
Affiliation:
Department of Aerospace Engineering, Defence Institute of Advanced Technology, Pune, 411025, Maharashtra, India
A. Misra
Affiliation:
Department of Aerospace Engineering, Defence Institute of Advanced Technology, Pune, 411025, Maharashtra, India
*
nlvrsnt_phd2015@diat.ac.in
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Abstract

The ability of microramps to control shock - boundary layer interaction at the vicinity of an axisymmetric compression corner was investigated computationally in a Mach 4 flow. A cylinder/flare model with a flare angle of 25° was chosen for this study. Height (h) of the microramp device was 22% of the undisturbed boundary layer thickness (δ) obtained at the compression corner location. A single array of these microramps with an inter-device spacing of 7.5h was placed at three different streamwise locations viz. 5δ, 10δ and 15δ (22.7h, 45.41h and 68.12h in terms of the device height) upstream of the corner and the variations in the flowfield characteristics were observed. These devices modified the separation bubble structure noticeably by producing alternate upwash and downwash regions in the boundary layer. Variations in the separation bubble’s length and height were observed along the spanwise (circumferential) direction due to these devices.

Keywords

Flareshock-induced separationmicrorampsmicro-vortex generatorsflow control
Type
Research Article
Information
The Aeronautical Journal , Volume 124 , Issue 1271 , January 2020 , pp. 121 - 149
Copyright
© Royal Aeronautical Society 2019 

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