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Study of Restricted Shock Separation Phenomena in a Thrust Optimized Parabolic Nozzle

Haidn, Oskar and Verma, S. B. (2009) Study of Restricted Shock Separation Phenomena in a Thrust Optimized Parabolic Nozzle. Journal of Propulsion and Power, Vol. 25 (no. 5). American Institute of Aeronautics and Astronautics (AIAA). ISBN 10.2514/1.42351

Full text not available from this repository.

Abstract

An experimental investigation has been carried out on a subscale thrust optimized parabolic nozzle (area ratio of 30) to study the flow characteristics prevalent during a partially formed restricted shock separation and a fully formed restricted shock separation condition, each of which are observed to be discrete in nature. Whereas the wall pressure signal near the nozzle exit randomly alternates between its value in the backflow region and that above ambient (i.e., flow randomly alternates between a free shock separation and restricted shock separation transition condition and vice versa) as a function of time for a partially formed restricted shock separation condition, the wall pressure in a fully formed restricted shock separation condition fluctuates in values above ambient in the region of flow reattachment. Further, the transient conditions of free shock separation to partially formed restricted shock separation and end-effect regime are studied in detail. The preceding transitions and retransitions suggest a variation in the relative axial positions of normal and separation shocks that favors a fully formed restricted shock separation to occur during shutdown. A second separation bubble is also observed in the restricted shock separation condition, the formation and opening of which is seen to contribute toward side-load peaks. Results also indicate that the separation shock translates back and forth (flapping motion) and experiences spanwise perturbations (rippling motion). The results are based on simultaneously acquired real-time wall pressure measurements, surface oil visualization technique, high-speed schlieren images, and signals from strain gauges installed on the nozzle bending tube.

Item URL in elib:https://elib.dlr.de/59893/
Document Type:Article
Title:Study of Restricted Shock Separation Phenomena in a Thrust Optimized Parabolic Nozzle
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Haidn, OskarOskar.Haidn (at) dlr.deUNSPECIFIED
Verma, S. B.UNSPECIFIEDUNSPECIFIED
Date:September 2009
Journal or Publication Title:Journal of Propulsion and Power
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:Vol. 25
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
ISBN:10.2514/1.42351
Status:Published
Keywords:parabolic nozzle, shock separation
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W - no assignment
DLR - Research area:Space
DLR - Program:W - no assignment
DLR - Research theme (Project):W - no assignment (old)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Technologie
Deposited By: Hanke, Michaela
Deposited On:08 Sep 2009 20:02
Last Modified:01 Dec 2018 19:46

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