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Book ChapterDOI

Shock Tunnels and Hypersonic Research in IISc, Bangalore

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TLDR
The Laboratory for Hypersonic and Shock wave Research (LHSR), Department of Aerospace Engineering, Indian Institute of Science (IISc), Bangalore is a dedicated centre for the research, among other domains of fluid dynamics, on the shock dominated phenomena as mentioned in this paper.
Abstract
The Laboratory for Hypersonic and Shock wave Research (LHSR), Department of Aerospace Engineering, Indian Institute of Science (IISc), Bangalore is a dedicated centre for the research, among other domains of fluid dynamics, on the shock dominated phenomena. More often than not, the focus of the research is on the flow phenomena at high enthalpies, which are addressed using the impulse facilities—shock tubes and tunnels. Ever since its inception as the High Enthalpy Aerodynamics Laboratory (HEAL) in the early 1970s the laboratory has pioneered in many domains of hypersonic and shock wave research in the country. The research from the laboratory has not only supported the hypersonic missions of national and global interests, but also has greatly contributed to the fundamental understanding of many aspects of high speed/shock dominated flows and their control. The present chapter describes the various shock tunnels in the laboratory and reviews some of the important research works carried out in these ground test facilities.

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References
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Book

Schlieren and shadowgraph techniques

TL;DR: A review of recent developments in shadowgraph and schlieren visualization can be found in this paper, where the authors present a detailed overview of the shadowgraph technique for flow visualization.

Simplified curve fits for the thermodynamic properties of equilibrium air

TL;DR: New improved curve fits for the thermodynamic properties of equilibrium air were developed, substantially improved over those of previous curve fits appearing in NASA CR-2470.
Journal ArticleDOI

Counterflow drag reduction by supersonic jet for a blunt body in hypersonic flow

TL;DR: In this article, the aerodynamic drag force is measured using the accelerometer based force balance system and the experimental measurements show about 30% −45% reduction in drag coefficient for different jet pressures.
Journal ArticleDOI

Dynamic calibration of force balances for impulse hypersonic facilities

TL;DR: In this article, deconvolution is used to infer aerodynamic forces on models in impulse hypersonic wind tunnels along with the theory behind the different calibration techniques applied to a single component stress-wave force balance.