DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Tracer based Shock Visualisation A new measurement technique

Gawehn, Thomas and Schodl, Richard (2006) Tracer based Shock Visualisation A new measurement technique. In: 13th International Symposium on Application of Laser Techniques to Fluid Mechanics (1047). 13th Int. Symp. on Applications of Laser Techniques to Fluid Mechanics, 2006-06-26 - 2006-06-29, Lissabon (Portugal).

This is the latest version of this item.

Full text not available from this repository.


Knowledge of the shock wave position is quantitative information which helps in gathering and understanding the character of transonic and supersonic flows. Therefore visualisation techniques such as the Schlieren method or holographic interferometry are applied to wind tunnel experiments where the structure of the flow field is essentially two dimensional. In this report a recently developed non-intrusive technique to analyse three dimensional shock configurations without the need of velocity measurements is introduced. Thereby, the optical set-up allows the application of the technique to test sections with restricted optical access, e.g. to transonic compressors with a complex geometry of the casings. Up to now, only point-wise measurement techniques have been used to analyse the air flow velocities inside of those machines. The shock wave generates an considerable increase in the density of the flow. If particles are added upstream of the shock, it can be assumed that the concentration of the particles increases nearly in the same way. To visualise this, a laser light sheet is brought into the test section and illuminates the particles. the scattered light is captured by a CCD camera so that the position of the shock wave can be determined. To analyse the three dimensional structure of a shock wave, the light sheet is moved perpendicular to the flow direction. This new measurement technique (called Tracer based Shock Visualisation, TSV) is applied ot both, a supersonic wedge flow at Ma = 2.43 and a more complex shock wave configuration in a transonic cascade flow at Ma = 1-09. The gathered results are conclusive with Schlieren photographs, numerical simulations and, in case of the casdade flow, also with the simultaneously recorded surface pressure distribution. The applicability of the measurement technique to a rotating compressor is discussed. The problem with those measurements is not only the restricted optical access but also the synchronization of the image capturing process wih´th the rotational speed of the rotor. Both problems have been covered within the development of the TSV technique.

Item URL in elib:https://elib.dlr.de/47795/
Document Type:Conference or Workshop Item (Speech)
Title:Tracer based Shock Visualisation A new measurement technique
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Journal or Publication Title:13th International Symposium on Application of Laser Techniques to Fluid Mechanics
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Event Title:13th Int. Symp. on Applications of Laser Techniques to Fluid Mechanics
Event Location:Lissabon (Portugal)
Event Type:international Conference
Event Dates:2006-06-26 - 2006-06-29
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Propulsion Systems (old)
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - no assignment (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Institute of Propulsion Technology > Engine Measurement Systems
Deposited By: Gawehn, Dr.-Ing. Thomas
Deposited On:19 Dec 2007
Last Modified:15 Jan 2010 00:27

Available Versions of this Item

  • Tracer based Shock Visualisation A new measurement technique. (deposited 19 Dec 2007) [Currently Displayed]

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Website and database design: Copyright © German Aerospace Center (DLR). All rights reserved.