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Shashi B. Verma

Researcher at Council of Scientific and Industrial Research

Publications -  65
Citations -  992

Shashi B. Verma is an academic researcher from Council of Scientific and Industrial Research. The author has contributed to research in topics: Mach number & Nozzle. The author has an hindex of 16, co-authored 65 publications receiving 754 citations. Previous affiliations of Shashi B. Verma include National Aerospace Laboratories & Indian Institute of Technology Kanpur.

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Shockwave/Boundary-Layer Interaction Control on a Compression Ramp Using Steady Micro Jets

TL;DR: In this article, an experimental investigation was conducted to control the amplitude of shock unsteadiness associated with a 24 deg compression-ramp-induced interaction in a Mach 2 flow.
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Performance Characteristics of an Annular Conical Aerospike Nozzle with Freestream Effect

TL;DR: In this paper, the effect of cowl length, plug length, and plug contour variation on the performance and base pressure characteristics of a Mach 2.0 annular conical aerospike nozzle with and without freestream flow was studied.
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Relation between shock unsteadiness and the origin of side-loads inside a thrust optimized parabolic rocket nozzle

TL;DR: In this article, an experimental test campaign has been carried out on a sub-scale thrust optimized parabolic (TOP) nozzle to study the relation between unsteady characteristics of separation and reattachment shocks and the origin of side-loads in rocket nozzles.
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Study of Restricted Shock Separation Phenomena in a Thrust Optimized Parabolic Nozzle

TL;DR: In this article, an experimental investigation has been carried out on a subscale thrust optimized parabolic nozzle (area ratio of======80230) to study the flow characteristics prevalent during a partially formed restricted shock separation and a fullyformed restricted separation condition, each of which are observed to be discrete in nature.
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Numerical study of shock/boundary layer interaction in supersonic overexpanded nozzles

TL;DR: In this article, a numerical study using a mixed finite element/finite volume method on unstructured meshes adapted for compressible flows is conducted to investigate turbulent boundary-layer separation in overexpanded subscale supersonic nozzles including shock/shock and shock/boundary layer interactions.