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Shock Tunnel Noise Measurement with Resonantly Enhanced Focused Schlieren Deflectometry

Parziale, N. J. and Jewell, J. S. and Shepherd, J. E. and Hornung, H. G. (2012) Shock Tunnel Noise Measurement with Resonantly Enhanced Focused Schlieren Deflectometry. In: 28th International Symposium on Shock Waves. Vol.1. Springer , Berlin, pp. 747-752. ISBN 978-3-642-25687-5.

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The character of the boundary layer noise and ambient tunnel noise are of interest in the experimental study of laminar to turbulent transition. The instability mechanism in hypersonic flow over slender bodies is the acoustic mode. A number of investigations of flow over a slender cone in high-enthalpy facilities have been performed; however, measurements of the boundary layer noise and ambient tunnel noise have not been made. In cold hypersonic facilities the frequency range of the acoustic mode typically lies below 500 kHz; in high-enthalpy facilities, 5-20 MJ/kg, the most strongly amplified acoustic mode frequency is approximately 1-3 MHz. These high frequencies are well beyond the reach of the piezo-electric pressure transducers typically used in cold hypersonic facilities. A logical approach is to investigate the use of optical methods. Measurements of the boundary layer noise and ambient tunnel noise on a five degree half angle cone in the Caltech T5 hypervelocity shock tunnel are made with a single point focused schlieren system and a resonantly enhanced focused schlieren system.

Item Type:Book Section
Related URLs:
URLURL TypeDescription ReadCube access
Parziale, N. J.0000-0001-9880-1727
Jewell, J. S.0000-0002-4047-9998
Shepherd, J. E.0000-0003-3181-9310
Hornung, H. G.0000-0002-4903-8419
Additional Information:© 2012 Springer-Verlag Berlin Heidelberg. This work was sponsored by AFOSR/National Center for Hypersonic Research in Laminar-Turbulent Transition, for which Dr. John Schmisseur is the program manager. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the Air Force Office of Scientific Research or the U.S. Government.
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)UNSPECIFIED
Subject Keywords:Turbulent Boundary Layer; Acoustic Mode; Shock Layer; Slender Body; Shock Tunnel
Record Number:CaltechAUTHORS:20200520-092004376
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:103348
Deposited By: Tony Diaz
Deposited On:20 May 2020 16:41
Last Modified:20 May 2020 16:41

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