Book ChapterDOI
Aerodynamic characteristics of generic flight vehicle configuration from shock tunnel tests
A. G. Sarwade,A. S. Narayana,S. Panneerselvam,N. Sahoo,S. Saravanan,Gopalan Jagadeesh,Kpj Reddy +6 more
Reads0
Chats0
TLDR
In this article, a generic flight vehicle configuration has been designed as a possible candidate for hypersonic flight, and the force coefficients over the test model configuration for different angles of attack are measured using a three-component accelerometer force balance system.Abstract:
A generic flight vehicle configuration has been designed as a possible candidate for hypersonic flight. Aerodynamic force coefficients over the test model configuration for different angles of attack are measured using a three-component accelerometer force balance system. Experiments are conducted in HST2 shock tunnel facility of IISc at an enthalpy of 2 MJ/kg and nominal Mach number of 6. This data will be useful for validating numerical results obtained by CFD techniques.read more
References
More filters
Book
Hypersonic and high temperature gas dynamics
TL;DR: In this article, the authors discuss the properties of high-temperature gas dynamics, including the effects of high temperature on the dynamics of Viscous Flow and Vibrational Nonequilibrium Flows.
Book
Low-Speed Wind Tunnel Testing
William H. Rae,Alan Pope +1 more
TL;DR: The use of wind tunnel data for aerodynamic experiments has been studied in this article, where three dimensions of three-dimensional flow and pressure, flow, and shear stress measurements are used to calibrate the test section.
Journal ArticleDOI
Three-component force balance for flows of millisecond duration
TL;DR: In this paper, the authors investigate the feasibility of a new type of multiple component force balance for measurements on models in hypervelocity hows of millisecond duration, which extends the concept of the single component stress-wave force balance to measurement of axial force, normal force, and pitching moment.
Journal ArticleDOI
An accelerometer balance system for measurement of aerodynamic force coefficients over blunt bodies in a hypersonic shock tunnel
TL;DR: A miniature three-component accelerometer balance system for measuring the fundamental aerodynamic force coefficients over blunt bodies has been designed, fabricated and tested in the Indian Institute of Science hypersonic shock tunnel HST2 at a nominal Mach number of 5.75 as mentioned in this paper.
Journal ArticleDOI
Multi-component force balances for conventional and cryogenic wind tunnels
TL;DR: In this paper, a review of the general literature on the subject of strain-gauge balances is presented, and some comments on the demand for high accuracy are given, as well as specific design features of cryogenic balances and half model balances.