Aerodynamic force measurements in shock tunnels using novel free floating balance system

Joarder, Ratan and Jagadeesh, G (2004) Aerodynamic force measurements in shock tunnels using novel free floating balance system. In: 42nd AIAA Aerospace Sciences Meeting and Exhibit, 5-8 January, 2004, Reno, Nevada.

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Abstract

A new free floating internally mountable balance system that ensures unrestrained motion of the model exposed to hypersonic flow in the shock tunnel has been designed, fabricated and tested. The drag force acting on a blunt leading edge flat plate has been measured using the new balance system. The model acceleration in the axial direction is measured using an accelerometer by ensuring unrestrained model motion during testing in the hypersonic shock tunnel. The balance has been calibrated by an impulse hammer. To measure the drag force, normal force and pitching moment of a typical hypersonic vehicle, another free floating balance configuration has been designed, fabricated and tested. Finite element modeling (FEM) and CFD are exhaustively used in the design and calibration of the two balances. The experimentally measured drag force on the blunt leading edge flat plate at nominal Mach number of 5.75 matches well with FEM results. The details of the study are described in this paper.

Item Type:	Conference Paper
Publisher:	American Institute of Aeronautics and Astronautics
Additional Information:	Copyright of this article belongs to American Institute of Aeronautics and Astronautics.
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	17 Feb 2008
Last Modified:	19 Sep 2010 04:42
URI:	http://eprints.iisc.ac.in/id/eprint/13046

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